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(1)ARRIEL 1. Training manual December 2000 Ref.: X 292 87 960 2. TURBOSHAFT ENGINE.

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(3) ARRIEL 1. Training Manual. FOREWORD This document provides, in a teaching form, all the information required for the operation and the maintenance of the ARRIEL 1 Turboshaft engine for training purposes only. It will not be updated, and if required, modifications will be included in a new issue.. TURBOMECA Training Centre This document is the property of TURBOMECA and it may not be copied without the express authority of TURBOMECA. For training purposes only © Copyright - TURBOMECA - 2000. 0.1 Edition : December 2000. FOREWORD.

(4) Training Manual. ARRIEL 1. SUMMARY 0 - Foreword. 9 - Starting. 1 - Introduction. 10 - Electrical system. 2 - Power plant. 11 - Engine installation. 3 - Engine 4 - Oil system. 12 - Operating limitations and procedures. 5 - Air system. 13 - Various aspects of maintenance. 6 - Fuel system. 14 - Maintenance procedures. 7 - Control system. 15 - Fault analysis and trouble shooting. 8 - Control and indication For training purposes only © Copyright - TURBOMECA - 2000. 16 - Checking of knowledge 0.2 Edition : December 2000. SUMMARY.

(5) ARRIEL 1. Training Manual. TABLE OF CONTENTS 3 - ENGINE. 0 - FOREWORD -. Summary ............................................ Table of contents ................................ List of abbreviations .......................... Conversion table ................................. 0.2 0.3 0.7 0.10. 1 - INTRODUCTION -. General information ........................... Training method ................................. Training aids ...................................... Training programme .......................... 1.2 1.4 1.6 1.8 to 1.12. 2 - POWER PLANT -. General presentation ......................... General description ........................... General operation .............................. Principle of adaptation to helicopter .. Main characteristics ........................... Design and development .................... For training purposes only © Copyright - TURBOMECA - 2000. 2.2 2.4 2.8 2.12 2.14 2.22 to 2.27. - Engine ................................................ - Axial compressor ............................... - Gas generator HP section ................... • Centrifugal compressor ................... • Combustion chamber....................... • Gas generator turbine ...................... - Power turbine ..................................... - Exhaust pipe ....................................... - Reduction gearbox ............................. - Transmission shaft and accessory gearbox ....................... • Transmission shaft - twin-engine version ............................................. • Transmission shaft - single engine version ............................................. • Accessory box .................................. 3.2 3.8 3.14 3.16 3.22 3.28 3.34 3.40 3.42 3.48 3.50 3.52 3.54 to 3.61. 4 - OIL SYSTEM - Oil system ......................................... 4.2 - Lubrication ........................................ 4.8. 0.3 Edition : December 2000. TABLE OF CONTENTS.

(6) Training Manual. ARRIEL 1. TABLE OF CONTENTS (CONTINUED) 6 - FUEL SYSTEM. 4 - OIL SYSTEM (CONTINUED) -. Oil tank ............................................. Oil pumps ........................................... Electrical magnetic plugs ................... Oil filter.............................................. Filter pre-blockage indicator .............. Oil cooler ........................................... Centrifugal breather ........................... Magnetic plugs ................................... Strainers ............................................. Indicating devices .............................. Oil pipes and ducts .............................. 4.12 4.14 4.20 4.24 4.30 4.34 4.36 4.40 4.42 4.44 4.50 to 4.51. 5 - AIR SYSTEM -. Air system ......................................... Internal air system ............................. Air tappings........................................ Compressor bleed valve ..................... Air tapping unions ............................. Air pipes .............................................. For training purposes only © Copyright - TURBOMECA - 2000. 5.2 5.4 5.8 5.10 5.18 5.20 to 5.21. - Fuel system ....................................... - Fuel Control Unit ............................... • Fuel pump ........................................ • Fuel filter ......................................... • Manual control ................................ • Metering unit ................................... - Overspeed and drain valve ................ - Start injector electro-valve ................. - Main injection system ........................ - Start injectors ..................................... - Combustion chamber drain valve ...... - Fuel pipes ............................................ 6.2 6.12 6.14 6.18 6.24 6.28 6.30 6.36 6.42 6.46 6.50 6.54 to 6.55. 7 - CONTROL SYSTEM - Control system ................................... • General ............................................ • Description ...................................... • Operation .......................................... 7.2 7.2 7.4 7.6 to 7.33. 0.4 Edition : December 2000. TABLE OF CONTENTS.

(7) ARRIEL 1. Training Manual. TABLE OF CONTENTS (CONTINUED) 8 - CONTROL AND INDICATION -. Manual control system ....................... Indicating system ............................... Speed indication ................................. Tachometer transmitters ..................... Speed probes (1E, 1K, 1S versions) .. Gas temperature indication ................ Thermocouple probes ........................ Thermocouple junction box (1S version) ........................................ Torque indication ............................... Torquemeter ....................................... Torque transmitter .............................. Miscellaneous indications ................... 10 - ELECTRICAL SYSTEM 8.2 8.6 8.8 8.10 8.14 8.16 8.18. - Electrical system ................................ - Electrical accessories ......................... - Power turbine overspeed safety system ................................................ - Power turbine overspeed sensor ........ - Tachometer box .................................. - Super contingency power system ...... - Electrical harnesses ............................. 8.20 8.22 8.24 8.26 8.28 to 8.35. 9 - STARTING -. Starting system ................................... Starter ................................................. Ignition system ................................... Ignition units ...................................... Igniter plugs ....................................... Ignition cables ..................................... For training purposes only © Copyright - TURBOMECA - 2000. 9.2 9.10 9.16 9.18 9.22 9.26 to 9.27. 10.2 10.4 10.6 10.10 10.14 10.24 10.28 to 10.29. 11 - ENGINE INSTALLATION -. Engine compartment .......................... Engine mounting ................................ Power drive ........................................ Air intake ........................................... Exhaust system .................................. Engine system interfaces ................... • Oil system ........................................ • Aircraft LP fuel system ................... • Manual controls ............................... • Air system ....................................... - Drain system ...................................... - Fire protection ..................................... 11.2 11.4 11.8 11.10 11.12 11.14 11.14 11.16 11.18 11.20 11.22 11.24 to 11.25. 0.5 Edition : December 2000. TABLE OF CONTENTS.

(8) ARRIEL 1. Training Manual. TABLE OF CONTENTS (CONTINUED) - Deep maintenance .............................. 14.62 - Repair and overhaul ........................... 14.64 to 14.65. 12 - OPERATING LIMITATIONS AND PROCEDURES - Operating limitations ......................... 12.2 - Operating procedures ........................ 12.6 to 12.9. 13 - VARIOUS ASPECTS OF MAINTENANCE -. Maintenance concept ......................... TBOs and life limits ........................... Preventive maintenance ..................... "On-condition" monitoring ................ Corrective maintenance ..................... Lubricants - Fuels - Materials ............ Tooling ............................................... Technical publications ....................... Product support ................................... 13.2 13.4 13.6 13.8 13.10 13.12 13.14 13.16 13.22 to 13.23. 14 - MAINTENANCE PROCEDURES - General ............................................... 14.2 - Inspection and check procedures ....... 14.4 - Removal and installation procedures . 14.52 For training purposes only © Copyright - TURBOMECA - 2000. 15 - FAULT ANALYSIS AND TROUBLE SHOOTING - Fault analysis ..................................... 15.2 - Trouble shooting ................................ 15.32 to 15.47. 16 - CHECKING OF KNOWLEDGE -. Introduction ........................................ Questionnaire 1 ................................. Questionnaire 2 ................................. Questionnaire 3 ................................. Questionnaire 4 ................................... 16.2 16.3 16.6 16.12 16.15 to 16.30. OBSERVATIONS ................................... Last page This training manual is established to meet training requirements and takes into consideration, to a certain extent, ATA 104 specifications. This document has 562 pages. It was produced using a desktop publishing system.. 0.6 Edition : December 2000. TABLE OF CONTENTS.

(9) Training Manual. ARRIEL 1. LIST OF ABBREVIATIONS The abbreviations / symbols shown below may be used during training : A/C ............... AC ................. ACMS ........... ACW ............. AEO .............. ATA .............. BITE ............. Tq (C) ........... cc/h ............... FCV .............. CH ................. cSt ................. CW ................ daN ............... dB ................. DC ................. DGAC ........... Ec .................. EGT ............... Aircraft Alternating Current Automatic Control Monitoring System Anti-clockwise All Engines Operating Air Transport Association Built In Test Equipment Torque Cubic centimetres per hour Frequency/Voltage Converter Hourly Fuel consumption Centistoke Clockwise DecaNewton Decibel Direct Current Direction Générale de l'Aviation Civile Kinetic energy Exhaust Gas Temperature. For training purposes only © Copyright - TURBOMECA - 2000. FAA .............. FCU .............. FMU ............. FOD .............. ft .................... FWD ............. G ................... g .................... HE ................. HP ................. HP ................. HUMS........... Hz ................. ICP ................ ID .................. IFDS ............. ILS ................ ISA ................ ISV ................. Federal Aviation Administration Fuel Control Unit Fuel Metering Unit Foreign Object Damage Feet Forward Mass air flow Gram High Energy Horse Power High Pressure Health and Usage Monitoring System Hertz Intermediate Contingency Power Identification Integrated Flight Display System Integrated Logistic Support International Standard Atmosphere Servo-valve intensity. 0.7 Edition : December 2000. LIST OF ABBREVIATIONS.

(10) Training Manual. ARRIEL 1. LIST OF ABBREVIATIONS (CONTINUED) kHz ............... kPa ................ kW ................ l/h .................. lb ................... lb/HP.hr ........ lb/hr ............... lb/sec. ............ LRU .............. LTT ............... LVDT ........... m ................... mA ................ MAX ............. MCP .............. MCQ ............. MGB ............. MHz .............. MIN .............. mm ................ mP .................. Kilohertz Kilopascal Kilowatt Litre per hour Pound Pounds per Horse Power per hour Pounds per hour Pounds per second Line Replaceable Unit Learning Through Teaching Linear Voltage Differential Transducer Metre Milliampere Maximum Max Continuous Power Multi Choice Questionnaire Main gearbox Mega Hertz Minimum Millimetre Micro-processor. For training purposes only © Copyright - TURBOMECA - 2000. MTBF ........... MTBUR ........ MTCP ........... MTTR ........... mV ................ N ................... N1 ................. N2 ................. NMD ............. NOVRAM .... NR ................. ω ................... O/S ................ OEI ............... P .................... P2 .................. POS ............... PPM .............. PSI ................ PSIA ............. PSID .............. Mean Time Between Failure Mean Time Between Unscheduled Removal Maintenance Test Control Panel Mean Time to Repair Millivolt Rotation speed Gas generator rotation speed Power turbine rotation speed Navigation and Mission Display Non Volatile Random Access Memory Rotor rotation speed Angular Velocity Overspeed One Engine Inoperative Pressure Compressor outlet pressure Position Parts per million Pounds per Square Inch Pounds per Square Inch Absolute Pounds per Square Inch Differential. 0.8 Edition : December 2000. LIST OF ABBREVIATIONS.

(11) ARRIEL 1. Training Manual. LIST OF ABBREVIATIONS (CONTINUED) PSIG ............. PT ................. Q ................... RAM ............. ROM ............. RPM .............. RTD .............. SCP ............... SFC ............... Shp ................ SI ................... SRU .............. t ..................... T/O ................ TBO .............. TET ............... TM ................ t° ................... t4 .................... Pounds per Square Inch Gauge Power Turbine Fuel flow Random Access Memory Read Only Memory Revolutions Per Minute Resistive Temperature Device Super Contingency power Specific Fuel Consumption Shaft horse power International System Shop replaceable unit Time Take-Off Time Between Overhauls Turbine Entry Temperature Turbomeca Temperature Gas temperature. For training purposes only © Copyright - TURBOMECA - 2000. US G ............. VAC .............. VDC .............. W .................. XTL .............. XCP .............. Z .................... Zp .................. °C .................. °F .................. °K .................. ± .................... Ω ................... ∆ .................... ∆P ................. % ................... < .................... > ..................... US Gallon Volt, Alternating Current Volt, Direct Current Power Throttle position signal Collective Pitch Signal Altitude Pressure altitude Degrees Celsius Degrees Fahrenheit Degrees Kelvin Plus or Minus Ohm Difference (delta) Pressure difference Percent Is lower than Is higher than. 0.9 Edition : December 2000. LIST OF ABBREVIATIONS.

(12) ARRIEL 1. Training Manual. CONVERSION TABLE UNIT. International System. Length. 1 mm 1m. = =. 0.039 inch 3.28 ft = 1.09 yard. Volume. 1 dm3 = 1 litre. =. 0.26 US gallon. Mass. 1 kg. =. 2.2 lbs. Power. 1 kW. =. 1.34 HP. Temperature. °C °K. = =. (°F-32). 5/9 [(°F-32)5/9] + 273. Pressure. 1 kPa = 0.01 bar. =. 0.145 PSI. Flow (air, oil, fuel). 1 kg/s. =. 2.2 lbs/sec.. Specific Fuel Consumption. 1 g/kW.h. =. 0.00164 lb/HP.hr. For training purposes only © Copyright - TURBOMECA - 2000. British or American Systems. 0.10 Edition : December 2000. CONVERSION TABLE.

(13) Training Manual. ARRIEL 1. 1 - INTRODUCTION - General information ...................................................... 1.2 - Training method ............................................................ 1.4 - Training aids .................................................................. 1.6 - Training programme .................................................... 1.8 to 1.12. For training purposes only © Copyright - TURBOMECA - 2000. 1.1 Edition : December 2000. INTRODUCTION.

(14) ARRIEL 1. Training Manual. Training Centre. GENERAL INFORMATION. The Training Centre is located in one of the buildings of TURBOMECA's TARNOS factory.. «The power of knowledge» Adequate training is essential for obvious safety reasons, but also to reduce additional maintenance costs incurred by unjustified removals and excessive downtime.. TARNOS ..... 5 kms north of the BAYONNE ANGLET - BIARRITZ district - Access by train (BAYONNE station), by plane (BIARRITZ-PARME airport), by road (A63 highway, TARNOS exit).. Address ....... TURBOMECA - 40220 TARNOS FRANCE. Telex ............ 570 042. Telephone ... (33) 5 59 74 40 07 or 05 59 74 40 07. Fax ............... (33) 5 59 74 45 15 or 05 59 74 45 15. E-mail .......... [email protected]. "Greater knowledge leads to greater efficiency".. Objectives of training The main objective is the acquisition of the knowledge required for the tasks to be achieved (know and know how). Further information is also communicated to widen the skill and the experience of the trainee.. Training approach - Performance based training according to task analysis, with classroom sessions, student involvement, practical work and troubleshooting techniques - Advanced training aids : training manual, Computer Aided Presentation (or overhead projection), multimedia courseware and demonstration mock-ups - Experienced and formally trained instructors - Courses are taught in English and French and, in special circumstances, in German and Spanish. For training purposes only © Copyright - TURBOMECA - 2000. The training centre is organized in order to answer to training demands (administration, training aids, instructors).. Training sites Training courses are also conducted in subsidiaries, in approved training centres and on site : - by a TURBOMECA qualified instructor, in certain subsidiaries and approved training centres - or by an instructor detached from TURBOMECA France, in our subsidiaries and in the clients' premises.. 1.2 Edition : December 2000. INTRODUCTION.

(15) ARRIEL 1. Training Manual. TRAINING OBJECTIVES OF TRAINING. «The power of knowledge» Adequate training is essential for obvious safety reasons, but also to reduce additional maintenance costs incurred by unjustified removals and excessive downtime.. TRAINING APPROACH. "Greater knowledge leads to greater efficiency".. TRAINING CENTRE, TURBOMECA Tarnos (FRANCE). FRANCE ATLANTIC OCEAN. TARNOS BAYONNE BORDES. SPAIN. PARIS. TRAINING SITES Training courses are also conducted in subsidiaries, in approved training centres and on site.. GENERAL INFORMATION For training purposes only © Copyright - TURBOMECA - 2000. 1.3 Edition : December 2000. INTRODUCTION.

(16) Training Manual. ARRIEL 1. TRAINING METHOD Knowledge transmission process. Training method. The required knowledge is transmitted in such a manner that the student may use it efficiently in various circumstances.. The training method is a carefully balanced combination of : - Lecture. The training is conducted in accordance with a process which considers :. - Discussions. - A phase of explanation for understanding. - Exercises. - A phase of assimilation leading to the complete acquisition and long-term retention of the knowledge.. - Practical work.. Continuous checking of knowledge helps to ensure the information is assimilated. It is more a method of work than a testing in the traditional sense (refer to chapter 16).. For training purposes only © Copyright - TURBOMECA - 2000. 1.4 Edition : December 2000. INTRODUCTION.

(17) ARRIEL 1. Training Manual. EXPLANATION. ASSIMILATION. 1 KNOWLEDGE TRANSMISSION, PHASES :. 2. MEDIA. 3. 4. - Explanation - Assimilation CHECKING OF KNOWLEDGE : - Continuous checking, treated in. 1 - LECTURE. chapter 16. 2 - EXERCISES 3 - DISCUSSIONS 4 - PRACTICAL WORK. INSTRUCTOR. STUDENT. KNOWLEDGE TRANSMISSION PROCESS. TRAINING METHOD. TRAINING METHOD For training purposes only © Copyright - TURBOMECA - 2000. 1.5 Edition : December 2000. INTRODUCTION.

(18) Training Manual. ARRIEL 1. TRAINING AIDS Training manual. Multimedia courseware. The training manual is the basic source of information.. Interactive courseware is used to transmit information during a course.. It contains, in a teaching form, all required information and explanations, following a layout derived from the ATA 104 standard. Thus each subject is treated following a plan which allows the material to be adapted to different levels of training.. This multimedia system uses text, photos, illustrations, animation and video. Certain courses are available for sale on CD-ROM. This system with quick and easy access can be very efficient for maintaining knowledge levels in the workplace.. Typical plan : - General (function, position, main characteristics, main components) - Description (general and detailed). However, only a course delivered by a TURBOMECA instructor or TURBOMECA qualified instructor would allow the issue of an engine maintenance authorisation card.. - Operation (phases, synthesis). Other technical publications are also used during a course.. Demonstration mock-ups are also used for component identification and maintenance procedures.. Computer Aided Presentation or overhead projection Computer Aided Presentation or overhead projection is used to display the illustrations contained in the training manual (the instructor's explanations follow the manual).. For training purposes only © Copyright - TURBOMECA - 2000. Demonstration mock-ups. Note : The information contained in the Training Aids must be considered for training purposes only.. 1.6 Edition : December 2000. INTRODUCTION.

(19) Training Manual. ARRIEL 1. TRAINING MANUAL Note : The information contained in the Training Aids must be considered for training purposes only.. MULTIMEDIA COURSEWARE. COMPUTER AIDED PRESENTATION OR OVERHEAD PROJECTION. DEMONSTRATION MOCK-UPS. TRAINING AIDS For training purposes only © Copyright - TURBOMECA - 2000. 1.7 Edition : December 2000. INTRODUCTION.

(20) Training Manual. ARRIEL 1. TRAINING PROGRAMME The course programme follows the manual. However, it should be noted that the "classroom sessions" alternate with periods devoted to demonstrations and practical work.. Examples of programme :. According to the contents, each session is mainly devoted to description and operation.. - Familiarization course. The engine maintenance aspect is mainly covered by the last part of the manual, which also deals with various elements related to maintenance (standard practices, technical publications, logistics and mainly fault analysis and fault finding).. The following pages provide examples of training programme :. - 1st line maintenance (O level) : preventive and corrective maintenance - 2nd line maintenance (I level) : modules, SRU - 3rd line maintenance (H level) : deep maintenance - 4th line maintenance (D level) : repair or overhaul.. For training purposes only © Copyright - TURBOMECA - 2000. 1.8 Edition : December 2000. INTRODUCTION.

(21) Training Manual. ARRIEL 1. FAMILIARIZATION COURSE Objective : At the end of this course, the student will be able to describe the engine, to explain its principle of operation and to identify the main components of the engine and systems. Programme :. - Introduction. FIRST DAY. - General presentation of the engine - Engine description - Engine systems. - Engine systems (continued). SECOND DAY. - Main aspects of maintenance - Revision - Checking of knowledge. For training purposes only © Copyright - TURBOMECA - 2000. 1.9 Edition : December 2000. INTRODUCTION.

(22) Training Manual. ARRIEL 1. 1st LINE MAINTENANCE COURSE (O LEVEL) : PREVENTIVE AND CORRECTIVE MAINTENANCE Objective : At the end of this course, the student will be able to identify the engine components, to describe and to explain the operation of the engine and its systems, to carry out 1st line maintenance procedures and to diagnose operating failures. Programme :. - Introduction - General. FIRST DAY - Engine presentation - Engine description - Oil system. SECOND DAY. - Air system - Fuel system - Control system - Measurement and indicating systems - Starting. THIRD DAY - Electrical system - Engine installation - Operating limitations and procedures - Various aspects of maintenance. FOURTH DAY - Maintenance procedures - Trouble shooting - Visits - Revision. FIFTH DAY - Examination - Miscellaneous questions. For training purposes only © Copyright - TURBOMECA - 2000. 1.10 Edition : December 2000. INTRODUCTION.

(23) Training Manual. ARRIEL 1. 2nd LINE MAINTENANCE COURSE (I LEVEL) : MODULES, SRU Objective : At the end of this course, the student will be able to identify the engine components, to carry out all the 2nd line maintenance procedures (mainly the removal/installation of modules and shop replaceable unit). Programme : The programme mainly includes practical work. This programme can be carried out after the 1st line maintenance programme.. - Introduction. FIRST DAY. - Revision (if this course is not conducted directly after the 1st line course) - Removal of modules - Removal of modules. SECOND DAY. - Inspection and check of modules - Installation of modules. THIRD DAY. For training purposes only © Copyright - TURBOMECA - 2000. - Inspection and checks after installation. 1.11 Edition : December 2000. INTRODUCTION.

(24) Training Manual. ARRIEL 1. 3rd LINE MAINTENANCE COURSE (H LEVEL) : DEEP MAINTENANCE Objective : At the end of the course, the trainee will be able to carry out the 3rd line maintenance procedures (deep maintenance). Programme :. - Introduction FROM 3 DAYS TO 3 WEEKS. - Definition of procedures - Practical work. 4th LINE MAINTENANCE COURSE (D LEVEL) : REPAIR OR OVERHAUL Objective : At the end of the course, the trainee will be able to carry out the specific tasks regarding the engine and related to his skills (eg : control system, assembly, machining procedures...). Programme :. - Introduction SEVERAL WEEKS. - Definition of procedures - Practical work. For training purposes only © Copyright - TURBOMECA - 2000. 1.12 Edition : December 2000. INTRODUCTION.

(25) Training Manual. ARRIEL 1. 2 - POWER PLANT - General presentation .................................................... 2.2 - General description ...................................................... 2.4 - General operation ........................................................ 2.8 - Principle of adaptation to helicopter ........................... 2.12 - Main characteristics ..................................................... 2.14 - Design and development .............................................. 2.22 to 2.27. For training purposes only © Copyright - TURBOMECA - 2000. 2.1 Edition : December 2000. POWER PLANT.

(26) Training Manual. ARRIEL 1. GENERAL PRESENTATION Function The power plant provides power by transforming the energy contained in the air and fuel into shaft power.. Main characteristics - Type : free turbine turboshaft engine, front power drive, external power transmission shaft - Concept : modular - Output shaft speed: 6000 RPM (at 100 %) (except the 1S1) - Mass ≈ 126 kg (277 lbs). The mass may vary according to the engine versions.. For training purposes only © Copyright - TURBOMECA - 2000. 2.2 Edition : December 2000. POWER PLANT.

(27) ARRIEL 1. Training Manual. GAS. AIR. POWER FUEL. 6000 RPM at 100 % (except 1S1). POWER PLANT - Free turbine type - Modular - Mass ≈ 126 kg (277 lbs). GENERAL PRESENTATION For training purposes only © Copyright - TURBOMECA - 2000. 2.3 Edition : December 2000. POWER PLANT.

(28) Training Manual. ARRIEL 1. ENGINE GENERAL DESCRIPTION This description considers the main functional components of the engine.. Transmission shaft. Gas generator. - External shaft located in a protecting tube which connects the reduction gearbox to the accessory gearbox.. - Single stage axial compressor. Accessory gearbox. - Centrifugal compressor. - Gearbox containing the accessory drive train and the main power drive.. - Annular combustion chamber with centrifugal fuel injection - Two stage axial turbine.. Power turbine - Single stage axial turbine.. Exhaust pipe - Elliptical, axial exhaust pipe.. Reduction gearbox - Reduction gearbox comprising three helical toothed gears.. For training purposes only © Copyright - TURBOMECA - 2000. 2.4 Edition : December 2000. POWER PLANT.

(29) ARRIEL 1. Training Manual. GAS GENERATOR Axial compressor. Centrifugal compressor. POWER TURBINE. Combustion chamber. EXHAUST PIPE. Turbine. ACCESSORY GEARBOX. MAIN POWER DRIVE. TRANSMISSION SHAFT. REDUCTION GEARBOX. ENGINE GENERAL DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 2.5 Edition : December 2000. POWER PLANT.

(30) Training Manual. ARRIEL 1. ENGINE SYSTEMS - GENERAL DESCRIPTION This part deals with the systems and functions of the engine.. Engine handling procedure Entirely automatic. Control lever to start, stop and for emergency control.. Oil system The oil system lubricates and cools the engine components.. Engine indicating. Dry sump system, synthetic oil, tank and cooling unit installed on the aircraft. Pressure, temperature and magnetic particles indications.. Rotation speeds. Gas temperature. Engine torque. Oil temperature and pressure. Miscellaneous indications.. Starting Air system Internal system to pressurise and cool engine internal parts. Accessory air supply system (ventilation of start injectors, engine control). Compressor bleed valve. Air supply to the aircraft.. Cranking by an electric starter. Ignition by High Energy. Manual control.. Electrical system Starting system. Indicating system. Overspeed system. Harness with two or three connectors according to version.. Fuel system Fuel supply through a gear type pump. Delivery through a metering unit and a valve. Start injection through 2 simple injectors. Main injection by a centrifugal wheel.. Control system. Engine installation - Interfaces designed for quick removal and installation of engine - Front and rear supports. Lifting rings. Constant power turbine rotation speed. Acceleration control. Miscellaneous protection systems.. - Miscellaneous equipment (air intake, exhaust, firewalls, transmission shaft, air bleeds, drains, fire protection).. Hydro-mechanical control system (with a mechanical back-up manual control) using fuel as hydraulic fluid.. For training purposes only © Copyright - TURBOMECA - 2000. 2.6 Edition : December 2000. POWER PLANT.

(31) ARRIEL 1. Training Manual. AIR SYSTEM. FUEL SYSTEM. OIL SYSTEM. CONTROL SYSTEM. ENGINE INSTALLATION. FWD. ENGINE HANDLING PROCEDURE. ELECTRICAL SYSTEM ENGINE INDICATING STARTING. ENGINE SYSTEMS - GENERAL DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 2.7 Edition : December 2000. POWER PLANT.

(32) Training Manual. ARRIEL 1. GENERAL OPERATION This part deals with the basic operation of the engine.. Transmission shaft. Gas generator. - Transmission of the power from the reduction gearbox to the output shaft.. - Compression of the air in the axial and centrifugal compressors - Combustion of the fuel/air mixture in the annular combustion chamber - Gas expansion in the gas generator turbine which drives the compressors and engine accessories.. Accessory gearbox - Power take-off to drive the helicopter main gearbox - Drive of the accessories by the gas generator through a bevel gear, a vertical drive shaft and a gear train.. Power turbine - Expansion of the gas in the single stage turbine which drives the output shaft through the reduction gearbox.. Exhaust - Discharge overboard of the gas.. Reduction gearbox - Drive, at reduced speed, to the transmission shaft.. For training purposes only © Copyright - TURBOMECA - 2000. 2.8 Edition : December 2000. POWER PLANT.

(33) ARRIEL 1. Training Manual. GAS GENERATOR COMPRESSION. COMBUSTION. POWER TURBINE EXPANSION. EXPANSION. GAS EXHAUST. AIR INLET. ACCESSORY GEARBOX ACCESSORY DRIVE. POWER DRIVE. FUEL. TRANSMISSION SHAFT. REDUCTION GEARBOX. FORWARD POWER TRANSMISSION. DRIVE SPEED REDUCTION. GENERAL OPERATION For training purposes only © Copyright - TURBOMECA - 2000. 2.9 Edition : December 2000. POWER PLANT.

(34) Training Manual. ARRIEL 1. OPERATION - ADAPTATION This part deals with the parameters and the adaptation of the gas generator and power turbine.. Component adaptation For the engine operation, two functional assemblies can be considered :. Power turbine The power turbine operation is defined by the balance between the power received from the gas generator and the torque applied on the shaft, that is the torque C and the rotation speed N2.. Operation. - The gas generator which provides kinetic energy - The power turbine which transforms the kinetic energy into mechanical power on a shaft.. The operation is represented by the diagram which shows the power W, the rotation speeds N1 and N2 and the max torque limit C imposed by the mechanical transmission :. The two assemblies have different rotation speeds.. - The torque C is a function of the N2 rotation speed. Gas generator. - The power W is equal to the torque C multiplied by the angular velocity ω. The gas generator operation is defined by : - The air mass flow G (air flow which enters the engine). - At constant N2 speed, the power is only a function of the torque. - The air pressure P2 and air temperature t2 at the centrifugal compressor outlet. - The engine parameters can be represented as a function of a reference parameter ; N1 for example.. - The fuel flow Q injected into the combustion chamber - The gas temperature TET at the turbine entry - The rotation speed N1 of the gas generator - The kinetic energy Ec supplied to the turbine.. For training purposes only © Copyright - TURBOMECA - 2000. 2.10 Edition : December 2000. POWER PLANT.

(35) ARRIEL 1. Training Manual GAS GENERATOR. POWER TURBINE C (shaft torque). N1 (rotation speed) Ec (kinetic energy). G (air mass flow). N2 rotation speed (constant) W (shaft power). P2, t2 (compressor outlet pressure and temperature). TET (turbine entry temperature) Q (fuel flow) ENGINE PARAMETERS. W. C. e qu. or xt. Isospeeds N1. Ma. W=C.ω ω=2 πN 60. G. 0 /P P2 W. CH T TE. SFC. N2 Power W and speeds N1, N2. N2 Torque as a function of N2. N1. P2/P0: Compression ratio CH : Hourly fuel consumption SFC : Specific fuel consumption. COMPONENT ADAPTATION. OPERATION - ADAPTATION For training purposes only © Copyright - TURBOMECA - 2000. 2.11 Edition : December 2000. POWER PLANT.

(36) Training Manual. ARRIEL 1. PRINCIPLE OF ADAPTATION TO HELICOPTER Power transmission. Installation requirements. The mechanical power supplied by the engine, is used to drive the helicopter rotors through a mechanical transmission.. The main functional requirements of the installation are : - Constant rotor rotation speed NR in all operating conditions. This power drives : - Max torque limit C (usually imposed by the aircraft transmission). - The main rotor (approximately 82 %) - The tail rotor (approximately 10 %). - Complete engine protection (N1 and N2 speeds, TET temperature, compressor surge ∆Q/∆t…). - The main gearbox (approximately 8 %).. - Good load sharing (in the case of a multi-engine configuration).. Twin engine configuration In a twin engine configuration, the engines are installed at the rear of the main gearbox. The power turbines of the two engines are mechanically connected to the main gearbox which drives the rotors (main and tail rotors).. For training purposes only © Copyright - TURBOMECA - 2000. Adaptation to requirements To have a constant rotation speed of the power turbine N2, the power supplied by the engine is automatically adapted to the demand. This adaptation is ensured by the control system which meters the fuel flow injected into the combustion chamber so as to deliver the required power (variation of the gas generator N1 rotation speed) while keeping the engine within its operational limits.. 2.12 Edition : December 2000. POWER PLANT.

(37) ARRIEL 1. Training Manual MAIN ROTOR 82%. MAIN GEARBOX. ENGINE 2. ENGINE 100%. TAIL ROTOR. ENGINE 1 MAIN GEARBOX 8%. TAIL ROTOR 10%. MAIN ROTOR. POWER TRANSMISSION. TWIN ENGINE CONFIGURATION. N2. W - Power. NR (constant) N1, N2, TET,. W. Q/ t N2 N2. time Max torque C. t. INSTALLATION REQUIREMENTS. ADAPTATION TO REQUIREMENTS. PRINCIPLE OF ADAPTATION TO HELICOPTER For training purposes only © Copyright - TURBOMECA - 2000. 2.13 Edition : December 2000. POWER PLANT.

(38) Training Manual. ARRIEL 1. MAIN CHARACTERISTICS (1) Mass, dimensions and identification Mass (dry) - Engine with specific equipment and without fluid : ≈ 126 kg (277 lbs) it may vary according to the engine version. Dimensions - Engine : • Length : 1166 mm (45.5 inches) • Width : 465.5 mm (18.2 inches) • Height : 609 mm (23.8 inches) Identification - Each module has an identification plate. - The identification plate of the complete engine is located on the module 1 protection tube.. For training purposes only © Copyright - TURBOMECA - 2000. 2.14 Edition : December 2000. POWER PLANT.

(39) ARRIEL 1. Training Manual. 609 mm (23.8 inches). 1166 mm (45.5 inches). POWER PLANT MASS (dry and with specific equipment) ≈ 126 kg (277 lbs). 465,5 mm (18.2 inches). TURBOMECA. 64320 BORDES - FRANCE Brevets SZYDLOWSKI. ARRIEL. Module référence. TURBOMECA. 64320 BORDES - FRANCE Brevets SZYDLOWSKI. ARRIEL Date Contrôles Certificat. P. kW. MASS, DIMENSIONS AND IDENTIFICATION. MAIN CHARACTERISTICS (1) For training purposes only © Copyright - TURBOMECA - 2000. 2.15 Edition : December 2000. POWER PLANT.

(40) Training Manual. ARRIEL 1. MAIN CHARACTERISTICS (2) Operational ratings The operational ratings correspond to given conditions of helicopter operation. The ratings are generally defined under determined speed and temperature conditions.. • Super contingency power (SCP or 1 min) : extreme rating used in place of max. contingency on some versions. Its limited use requires particular maintenance practices.. The following operational ratings are considered : - AEO ratings (All Engines Operating) : • Max take-off power (T/O) : max rating which can be used during take-off. This rating has a limited duration (5 minutes continuous) • Max continuous power (MCP) : rating which can be used without time limitation (this does not imply that it is used permanently) - OEI ratings (One Engine Inoperative) : • Max contingency power (MCP) : rating which can be used in the case of one engine failure during take-off or landing. This rating is usually limited to a period of continuous operation : 2 minutes 30 seconds. • Intermediate contingency power (ICP) : rating which can be used in the case of one engine failure in flight. This rating is usually limited to 30 minutes or unlimited. For training purposes only © Copyright - TURBOMECA - 2000. 2.16 Edition : December 2000. POWER PLANT.

(41) ARRIEL 1. Training Manual. W. A.E.O. RATINGS. O.E.I. RATINGS MAX CONTINGENCY POWER (MCP). T/O. 5 minutes. MAX CONTINUOUS POWER (MCP). 2 minutes 30 seconds. SCP. INTER CONTINGENCY POWER (ICP). unlimited. 1 minute. OPERATIONAL RATINGS. MAIN CHARACTERISTICS (2) For training purposes only © Copyright - TURBOMECA - 2000. 2.17 Edition : December 2000. POWER PLANT.

(42) Training Manual. ARRIEL 1. MAIN CHARACTERISTICS (3) Factors which affect performance. Evolution of specific fuel consumption (SFC). The engine performance is affected by flight and atmospheric conditions. The effects of these conditions are usually indicated by graphs which show the evolution of performance as a function of parameters likely to modify it (example : atmospheric temperature t0 and pressure altitude Z).. The specific fuel consumption varies with the operating conditions.. Power evolution (W). The specific fuel consumption decreases, when the power (W) increases (better thermal efficiency). For this type of installation, the specific fuel consumption which is mostly considered is that at the cruise rating.. The power delivered by the engine decreases when the altitude (Z) and the temperature (t0) increase (this is due to the air mass flow decrease through the engine). The conditions of the engine installation on the aircraft should also be noted (miscellaneous losses due to installation) as well as the flight conditions (essentially the aircraft speed). Evolution of fuel consumption (CH) The fuel consumption decreases at a given rating, when the altitude (Z) and the temperature (t0) increase.. For training purposes only © Copyright - TURBOMECA - 2000. 2.18 Edition : December 2000. POWER PLANT.

(43) ARRIEL 1. Training Manual. W (kW). CH. Z=. Z=. 600 0m. 0m. Z=. (0. Z=. (19. 680. -. + 15 °C (59 °F). 0m. ft). ft). 60 00. m. (0. ft). (19 68 0f t). t0. t0. EVOLUTION OF POWER (W). EVOLUTION OF FUEL CONSUMPTION (CH). SFC (g/kW.h) A = Cruise condition A. W (kW). EVOLUTION OF SPECIFIC FUEL CONSUMPTION (SFC). FACTORS WHICH AFFECT PERFORMANCE. MAIN CHARACTERISTICS (3) For training purposes only © Copyright - TURBOMECA - 2000. 2.19 Edition : December 2000. POWER PLANT.

(44) Training Manual. ARRIEL 1. MAIN CHARACTERISTICS (4) Engine operating envelope. Limitations. The engine is designed to operate within a given climatic envelope.. The engine operates within various limitations : rotation speeds, temperatures, pressures…. The envelope is defined by :. Refer to corresponding chapters and official publications.. - The atmospheric temperature t0 - The pressure altitude Zp - And lines of standard atmosphere. Flight envelope The flight envelope is illustrated by the t0/Zp diagram and the lines of standard atmosphere, with the max tropical zone and the min arctic zone. Engine starting envelope The starting and relight envelope is defined in the same way, but it is also affected by the specifications of oil and fuel used, and sometimes by particular procedures.. For training purposes only © Copyright - TURBOMECA - 2000. 2.20 Edition : December 2000. POWER PLANT.

(45) ARRIEL 1. Training Manual. ISA - International standard atmosphere. *. Max - Tropical zone t0. Min - Arctic zone. °C. +50°. t0. Depending on oil and fuel specifications. Can also require special operating procedures.. °C. +50°. Max. +15°. Max. ISA Min. -50°. -500 0. ISA. * -50°. Min. Zp. FLIGHT ENVELOPE. Zp. STARTING ENVELOPE. ENGINE OPERATING ENVELOPE. MAIN CHARACTERISTICS (4) For training purposes only © Copyright - TURBOMECA - 2000. 2.21 Edition : December 2000. POWER PLANT.

(46) Training Manual. ARRIEL 1. DESIGN AND DEVELOPMENT (1) Principles of design. Development steps. The engine is designed to meet the aircraft propulsion requirements and particularly for the new generation of helicopters.. - Certification in 1977 by the French Authorities. - The first production engine was delivered in January 1978.. The engine design is based on : - ARRIEL engines will be in service far beyond 2000. - An optimised thermodynamic cycle which gives high performance - Simple and reliable components giving a good supportability, and a good maintainability to reduce the costs.. Engine development. - Example : ARRIEL 1A2. ARRIEL - According to TURBOMECA tradition : name of a Pyrenean lake. - 1 : Type. The ARRIEL engine is based on research and experience of other engines : - First generation engines : ASTAZOU, ARTOUSTE and TURMO. For training purposes only © Copyright - TURBOMECA - 2000. Engine designation. - A : Variant - 2 : Version.. 2.22 Edition : December 2000. POWER PLANT.

(47) ARRIEL 1. Training Manual. Engine design. Optimised thermodynamic cycle. ARRIEL 1 650 - 700 Shp. Simple and reliable components. Supportability Maintainability. ASTAZOU 500 - 1000 Shp ARTOUSTE 400 - 850 Shp. High performance. Cost reduction. TURMO 1500 - 1600 Shp. ENGINE DEVELOPMENT. PRINCIPLES OF DISIGN In service far beyond 2000. STEPS 1978. ARRIEL lake. First production. 1977 Certification. TIME. Example : ARRIEL 1A2 ARRIEL : Name of a Pyrenean lake for the turboshaft engines 1 : Type A : Variant 2 : Version. ENGINE DESIGNATION. DEVELOPMENT STEPS. DESIGN AND DEVELOPMENT (1) For training purposes only © Copyright - TURBOMECA - 2000. 2.23 Edition : December 2000. POWER PLANT.

(48) Training Manual. ARRIEL 1. DESIGN AND DEVELOPMENT (2) Application. Engine fleet status. The ARRIEL 1 is presently destined for the following helicopters : Squirrel and Dolphin (EUROCOPTER), A 109 K2 (Agusta), S 76 (Sikorsky), BK 117 (MBB).. At the beginning of ..., we can note : - Number of ARRIEL 1 engines produced : ................ - Number of ARRIEL 1 engines in operation : ............ Maintenance concept. - Operating hours : ........................................................ The ARRIEL is designed to provide a high availability rate with reduced maintenance costs. The main aspects of the maintenance concept are the following : - Full modularity - Good accessibility - Reduced removal and installation times - "On condition" monitoring - High initial TBO - Low cost of ownership : • Low production costs • Durability (TBO, defined and proven life limits) • High reliability • Low fuel consumption.. For training purposes only © Copyright - TURBOMECA - 2000. 2.24 Edition : December 2000. POWER PLANT.

(49) ARRIEL 1. Training Manual. PT-HALB. S 76 (SIKORSKY). SQUIRREL (EUROCOPTER). CONOCO. G-BKXD SA 365 N. Management Aviation. BK 117 (MBB). DOLPHIN (EUROCOPTER). MAINTENANCE CONCEPT REGA I-RAIE. - Actual modularity. A 109 K2 (AGUSTA). - Good accessibility - Reduced time of removal and installation. FLEET STATUS. - Condition monitoring. - Arriel 1 engines produced. - High initial TBO. - Arriel 1 engines in service. - Low cost of ownership. - Operating hours. DESIGN AND DEVELOPMENT (2) For training purposes only © Copyright - TURBOMECA - 2000. 2.25 Edition : December 2000. POWER PLANT.

(50) Training Manual. ARRIEL 1. DESIGN AND DEVELOPMENT (3) ARRIEL family The great diversity of ARRIEL 1 operation is represented in the table below including : - Certification year - Version - Helicopter type - Engine power - Differences. For training purposes only © Copyright - TURBOMECA - 2000. 2.26 Edition : December 2000. POWER PLANT.

(51) ARRIEL 1. Training Manual. ARRIEL 1A. DOLPHIN 365 C. 651 shp (2' 30"). ARRIEL 1B. SQUIRREL AS 350 B. 640 shp (5'). ARRIEL 1A1. DOLPHIN 365 C1. 667 shp (2' 30"). max N1, W and flight envelope increased. ARRIEL 1A2. DOLPHIN 365 C2. 670 shp (2' 30"). New centrifugal compressor. 1980 ARRIEL 1C. DOLPHIN 365 N DOLPHIN 365 C3. 700 shp (2' 30"). Gas generator turbine with fir-tree mounted blades, new combustion chamber, increased N2. 1982 ARRIEL 1C1. DOLPHIN 365 N1. 723 shp (2' 30"). 1983 ARRIEL 1M. DOLPHIN 365 F. 777 shp (2' 30"). ARRIEL 1K. AGUSTA A 109 K. 723 shp (2' 30"). ARRIEL 1D. SQUIRREL AS 350 B1/L1. 683 shp (5'). ARRIEL 1S. SIKORSKY S 76 A. 772 shp (2' 30"). 1977. 1979. 1985. 1986. ARRIEL 1 MN DOLPHIN 365 F ARRIEL 1 D1 SQUIRREL AS 350 B2/L2 1988 ARRIEL 1 M1 PANTHER 365 K ARRIEL 1 C2 DOLPHIN 365 N2. 777 shp (2' 30"). 1991 ARRIEL 1E. 760 shp (2' 30"). BK 117. Free wheel, long exhaust pipe. Turbine materials, power turbine bearing modified 1 minute rating Adaptation to Agusta aircraft Max fuel flow limit Free wheel, power turbine support and exhaust pipe of the 1B Sealed turbine blades Adaptation to Sikorsky aircraft (support, transmission, systems...).. 1S standard. Adaptation to the BK 117. ARRIEL FAMILY. DESIGN AND DEVELOPMENT (3) For training purposes only © Copyright - TURBOMECA - 2000. 2.27 Edition : December 2000. POWER PLANT.

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(53) Training Manual. ARRIEL 1. 3 - ENGINE - Engine ............................................................................. - Axial compressor ........................................................... - Gas generator HP section.............................................. • Centrifugal compressor ............................................................. • Combustion chamber ................................................................. • Gas generator turbine ................................................................ - Power turbine................................................................. - Exhaust pipe................................................................... - Reduction gearbox......................................................... - Transmission shaft and accessory gearbox ................. • Twin-engine transmission shaft................................................. • Single engine transmission shaft ............................................... • Accessory gearbox ....................................................................... For training purposes only © Copyright - TURBOMECA - 2000. 3.2 3.8 3.14 3.16 3.22 3.28 3.34 3.40 3.42 3.48 3.50 3.52 3.54 to 3.61 3.1. Edition : December 2000. ENGINE.

(54) ARRIEL 1. Training Manual. ENGINE - GENERAL Function. Main components. The engine transforms the energy in the air and fuel into mechanical power on a shaft.. - Gas generator. Main characteristics - Type : Free turbine with forward drive via an external shaft - Power class : from 480 to 560 kW (650 to 760 Shp) according to version - Specific fuel consumption : according to version (see maintenance manual) - Gas generator speed (N1) : approximately 52000 RPM at 100 % • Direction of rotation : anti-clockwise. • Axial compressor (module M02) • HP section (module M03) - Centrifugal compressor - Annular combustion chamber - Two stage turbine - Single stage power turbine (module M04) - Exhaust pipe - Reduction gearbox (module M05) - Transmission shaft and accessory gearbox (module M01).. - Power turbine speed (N2) : 41586 RPM at 100 % • Direction of rotation : clockwise - Output shaft speed : 6000 RPM at 100 % (except the 1S1) • Direction of rotation : clockwise. Note : Direction of rotation given viewed from the rear.. For training purposes only © Copyright - TURBOMECA - 2000. 3.2 Edition : December 2000. ENGINE.

(55) ARRIEL 1. Training Manual. AXIAL COMPRESSOR. CENTRIFUGAL COMPRESSOR. COMBUSTION CHAMBER. TURBINE. POWER TURBINE. EXHAUST PIPE. Type : Free turbine Power class : From 480 to 560 kW (650 to 760 Shp) Specific fuel consumption : According to version Gas generator speed (N1) : Approximately 52000 RPM at 100% (ACW) Power turbine (N2) : 41586 RPM at 100% (CW) Output shaft : 6000 RPM at 100% (CW) except 1S1 TRANSMISSION SHAFT AND ACCESSORY GEARBOX. REDUCTION GEARBOX. ENGINE - GENERAL For training purposes only © Copyright - TURBOMECA - 2000. 3.3 Edition : December 2000. ENGINE.

(56) ARRIEL 1. Training Manual. ENGINE - DESCRIPTION Main components. Modular layout. - Gas generator • Axial compressor • Centrifugal compressor • Combustion chamber • Two stage turbine. The engine comprises 5 modules : - Module M01 : Transmission shaft and accessory gearbox - Module M02 : Axial compressor - Module M03 : Gas generator HP section. - Single stage power turbine. - Module M04 : Power turbine. - Exhaust pipe. - Module M05 : Reduction gearbox.. - Reduction gearbox - Transmission shaft. Note : A module is a sub-assembly which can be replaced on-site (2nd line maintenance) without complex tooling or adaptation work.. - Accessory gearbox.. Note : Some accessories are provided with each module.. Each module has an identification plate. The engine identification plate is fitted on the right hand side of the M01 protection tube.. In this manual, those components are dealt with in the chapters corresponding to the main systems.. For training purposes only © Copyright - TURBOMECA - 2000. 3.4 Edition : December 2000. ENGINE.

(57) ARRIEL 1. Training Manual. MODULE M02 AXIAL COMPRESSOR. MODULE M04 POWER TURBINE MODULE M03 GAS GENERATOR HIGH PRESSURE SECTION. MODULE M01 TRANSMISSION SHAFT AND ACCESSORY GEARBOX. MODULE M05 REDUCTION GEARBOX. ENGINE - DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 3.5 Edition : December 2000. ENGINE.

(58) ARRIEL 1. Training Manual. ENGINE - OPERATION The engine provides power by transforming the energy in the air and fuel into mechanical energy on a shaft. The process comprises compression, combustion, expansion and the transmission of the power.. Expansion - The gas expands in the gas generator turbine which extracts the energy required to drive the compressor and accessories (N1 rotation : 52000 RPM ACW) During this phase the pressure and temperature of the gas drop, whilst the velocity increases.. Compression The ambient air is compressed by an axial supercharging compressor and a centrifugal compressor. This phase is essentially characterised by the air flow (approx. 2.5 kg/s ; 5.5 lbs/sec.) and the compression ratio (approx. 8.2).. Combustion. - There is a further expansion in the power turbine which extracts most of the remaining energy to drive the output shaft (N2 rotation : 41586 RPM CW) After the power turbine the gas is discharged overboard via the exhaust pipe, giving a slight residual thrust.. Power transmission. The compressed air is admitted into the combustion chamber, mixed with the fuel and burnt in a continuous process.. The power is transmitted forward by a reduction gearbox and an external transmission shaft.. The air is divided into two flows : Note : The engine reference stations are :. - A primary flow for combustion - A secondary flow for cooling the gas. This phase is essentially characterised by the temperature rise, flame temperature approx. 2500 °C and turbine entry temperature of approx. 1100 °C, and a pressure drop of about 4 %.. For training purposes only © Copyright - TURBOMECA - 2000. 0 1 1' 2 3 4 5. -. Air intake Axial compressor inlet Axial compressor outlet Centrifugal compressor outlet Turbine inlet Gas generator turbine outlet Power turbine outlet.. 3.6 Edition : December 2000. ENGINE.

(59) ARRIEL 1. Training Manual. Primary air Residual thrust ≈ 15 daN (33 lbs). Gas Secondary air. AIR FLOW 2.5 kg/s (5.5 lbs/s). EXHAUST. 2500 (4532) 0. 1. 1'. 2. 3. 101,3 P kPa (14.7) (PSI) t °C (°F) V. 800 (116). 600 (1080). POWER TRANSMISSION (power transmitted forward by a reduction gearbox and an external shaft). 300 (43.5). 320 (608) 108 (15.7). 65 (149). 15 (59). AIR INLET. 5. 1125 (2057) 880 (1616). 820 (118.9) 160 (23.2). 4. Values given for information at a given reference rating COMPRESSOR. COMBUSTION CHAMBER. COMPRESSION. COMBUSTION. TURBINES EXPANSION. ENGINE - OPERATION For training purposes only © Copyright - TURBOMECA - 2000. 3.7 Edition : December 2000. ENGINE.

(60) ARRIEL 1. Training Manual. AXIAL COMPRESSOR - GENERAL Function. Main components. The axial compressor ensures a first stage of compression to supercharge the centrifugal compressor.. - Rotating components. Position - At the front of the engine (the axial compressor assembly forms the module M02).. • Air inlet cone • Axial wheel, shaft, bearing and accessory drive shaft - Stationary components • Diffuser • Casing.. Main characteristics - Type : axial transonic supercharging compressor - Air flow : 2.5 kg/sec (5.5 lbs/sec.) - Outlet pressure : 160 kPa (23.2 PSI) - Outlet temperature : 65 °C (149 °F). For training purposes only © Copyright - TURBOMECA - 2000. 3.8 Edition : December 2000. ENGINE.

(61) ARRIEL 1. Training Manual. WHEEL. DIFFUSER. SHAFT. Type : Axial transonic supercharging compressor Air flow : 2.5 kg/s (5.5 lbs/sec.) Outlet pressure : 160 kPa (23.2 PSI) Outlet temperature : 65 °C (149 °F). AIR INLET CONE. BEARING. CASING. ACCESSORY DRIVE SHAFT. AXIAL COMPRESSOR - GENERAL For training purposes only © Copyright - TURBOMECA - 2000. 3.9 Edition : December 2000. ENGINE.

(62) Training Manual. ARRIEL 1. AXIAL COMPRESSOR - DESCRIPTION The axial compressor module (module M02) includes rotating and stationary components.. Stationary components The stationary assembly includes the diffuser and the casing.. Rotating components The rotating assembly comprises the shaft, the inlet cone, the axial wheel and the accessory drive gear. The inlet cone, made of light alloy, is screwed into the front of the shaft. The compressor wheel is fitted to the shaft. It is a disc made of titanium alloy with blades cut from the solid. The shaft connects the centrifugal compressor to the axial compressor. The shaft is secured by a nut onto the tie-bolt. This assembly is supported by two bearings : a ball bearing at the rear of the axial compressor and a ball bearing in a flexible cage at the front of the centrifugal compressor.. The diffuser (diffuser-straightener) welded inside the casing has two rows of steel stator vanes which form a divergent passage for the air. The casing, made of steel, houses all the compressor components. It has a front flange for the mounting of the air inlet duct and a rear flange for the attachment to the module M03. The inner hub of the casing provides the location for the bearings. The casing has a boss for the mounting of the compressor bleed valve. The module identification plate is located at the front of the casing.. The accessory drive consists of a bevel gear on the shaft which drives a vertical drive shaft.. For training purposes only © Copyright - TURBOMECA - 2000. 3.10 Edition : December 2000. ENGINE.

(63) ARRIEL 1. Training Manual WHEEL. BEARING. DIFFUSER. NUT. TIE-BOLT IDENTIFICATION PLATE. SHAFT. ACCESSORY DRIVE GEAR INLET CONE. CASING CASING DIFFUSER WHEEL SHAFT. INLET CONE. AXIAL COMPRESSOR - DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 3.11 Edition : December 2000. ENGINE.

(64) Training Manual. ARRIEL 1. AXIAL COMPRESSOR - OPERATION The axial compressor ensures a first stage of compression in order to supercharge the centrifugal compressor.. Compressor air flow The ambient air, admitted through the air intake duct and guided by the inlet cone, flows between the blades of the axial compressor. The air is discharged rearwards with an increased axial velocity. The air then flows through the vanes of the diffuser. Due to the divergent passage, the air velocity is reduced and the pressure increased.. Operating parameters In standard conditions, the air flow is 2.5 kg/s (5.5 lbs/ sec.), the outlet pressure 160 kPa (23.2 PSI) and the outlet temperature 65 °C (149 °F). The rotation speed of the axial compressor wheel is obviously the gas generator speed. In order to avoid compressor surge, a valve discharges overboard a certain amount of air in certain operating conditions (refer to "AIR SYSTEM" chapter for further details on the compressor bleed valve).. The flow is straightened by the stator vanes before being admitted, through an annular duct, to the centrifugal compressor.. For training purposes only © Copyright - TURBOMECA - 2000. 3.12 Edition : December 2000. ENGINE.

(65) ARRIEL 1. Training Manual. ACCELERATION OF THE AIR. COMPRESSION AND STRAIGHTENING OF THE AIR. P1' : AIR DISCHARGED THROUGH THE COMPRESSOR BLEED VALVE. ADMISSION OF AMBIENT AIR (2.5 kg/s / 5.5 lbs/sec.). SUPERCHARGING OF THE CENTRIFUGAL COMPRESSOR (160 kPa / 23.2 PSI ; 6 °C / 149 °F). AXIAL COMPRESSOR - OPERATION For training purposes only © Copyright - TURBOMECA - 2000. 3.13 Edition : December 2000. ENGINE.

(66) Training Manual. ARRIEL 1. GAS GENERATOR HP SECTION Function. Main components. The HP section of the gas generator ensures the phases of compression (second stage), combustion and expansion (first stage).. - Centrifugal compressor. It provides the energy necessary to drive the power turbine.. - Turbine.. Position - It forms the module M03 and is mounted between the module M02 (axial compressor) and the module M04 (power turbine).. - Combustion chamber. Note : The power turbine nozzle guide vane belongs to the module M03.. Main characteristics - Identification plate on the turbine casing. For further information, refer to following pages.. For training purposes only © Copyright - TURBOMECA - 2000. 3.14 Edition : December 2000. ENGINE.

(67) ARRIEL 1. Training Manual. COMBUSTION CHAMBER. TURBINE. IDENTIFICATION PLATE. CENTRIFUGAL COMPRESSOR. GAS GENERATOR HP SECTION For training purposes only © Copyright - TURBOMECA - 2000. 3.15 Edition : December 2000. ENGINE.

(68) Training Manual. ARRIEL 1. CENTRIFUGAL COMPRESSOR - GENERAL Function. Main components. The compressor supplies the compressed air required for combustion.. - Rotating components (wheel, shaft, bearing) - Stationary components (diffusers, casings).. Supercharged by the axial compressor, it ensures the second stage of compression.. Position - At the front of the module M03.. Main characteristics - Type : centrifugal, high efficiency - Air flow : 2.5 kg/s (5.5 lbs/sec.) - Compression ratio : 5.4/1 (global : 8.2/1) - Outlet temperature : 320 °C (608 °F). For training purposes only © Copyright - TURBOMECA - 2000. 3.16 Edition : December 2000. ENGINE.

(69) Training Manual. ARRIEL 1. CASINGS. DIFFUSERS. BEARING. Type : Centrifugal, high efficiency TIE-BOLT. Air flow : 2.5 kg/s (5.5 lbs/sec.) Compression ratio : 5.4 / 1 (global : 8.2 / 1) Outlet temperature : 320 °C (608 °F) CENTRIFUGAL WHEEL. CENTRIFUGAL COMPRESSOR - GENERAL For training purposes only © Copyright - TURBOMECA - 2000. 3.17 Edition : December 2000. ENGINE.

(70) Training Manual. ARRIEL 1. CENTRIFUGAL COMPRESSOR DESCRIPTION The centrifugal compressor assembly includes rotating and stationary components.. Rotating components The main rotating component is the centrifugal wheel. The wheel has blades which are cut from the solid in a disc of titanium alloy and has a labyrinth seal on the rear shaft. The front part of the wheel connects to the axial compressor shaft. The rear part has a curvic-coupling for the mounting of the centrifugal fuel injection wheel. The rotating components are secured by a tie-bolt.. For training purposes only © Copyright - TURBOMECA - 2000. Stationary components The stationary assembly includes the diffusers and the casings. The compressor front cover is mounted inside the external casing by means of a ring of bolts which also secure the axial compressor casing, the front cover and the diffuser assembly. The external casing of the centrifugal compressor is bolted to the turbine casing. It is provided with several bosses for air bleeds. The diffuser assembly comprises the first stage diffuser (radial stator vanes) and the second stage diffuser (axial stator vanes). The diffuser back-plate forms a partition between the compressor and the combustion chamber. The fuel injection system is mounted on its inner hub.. 3.18 Edition : December 2000. ENGINE.

(71) ARRIEL 1. Training Manual. 1st STAGE DIFFUSER WHEEL. 2nd STAGE DIFFUSER. DIFFUSER ASSEMBLY LABYRINTH SEAL. COMPRESSOR FRONT COVER. BEARING TIE-BOLT. CURVIC COUPLING WHEEL FUEL INJECTION SYSTEM EXTERNAL CASING. EXTERNAL CASING. COMPRESSOR FRONT COVER. CENTRIFUGAL COMPRESSOR - DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 3.19 Edition : December 2000. ENGINE.

(72) Training Manual. ARRIEL 1. CENTRIFUGAL COMPRESSOR OPERATION The centrifugal compressor ensures the main stage of compression.. Compressor air flow The air supplied by the axial compressor flows between the blades of the centrifugal compressor. The air pressure increases due to the divergent passage between the blades and the air velocity increases due to the centrifugal flow.. Operating parameters In standard conditions, the air flow is 2.5 kg/s (5.5 lbs/ sec.), the compression ratio 5.4 (total 8.2), the outlet pressure 820 kPa (118.9 PSI) and the outlet temperature 320 °C (608 °F). The compressor wheel rotation speed is obviously the gas generator speed.. The air leaves the tips of the blades at very high velocity and then flows through the first stage diffuser vanes where the velocity is decreased and the pressure is increased. The air then passes through an elbow and the flow becomes axial. In the second stage diffuser, the velocity is again decreased and the pressure increased. The air is then admitted into the combustion chamber.. For training purposes only © Copyright - TURBOMECA - 2000. 3.20 Edition : December 2000. ENGINE.

(73) ARRIEL 1. Training Manual. COMPRESSION OF THE AIR IN THE DIFFUSERS ACCELERATION AND COMPRESSION OF THE AIR. AIR ADMITTED INTO THE COMBUSTION CHAMBER (820 kPa / 118.9 PSI ; 320 °C / 608 °F). SUPERCHARGING BY THE AXIAL COMPRESSOR (2.5 kg/s / 5.5 lbs/sec. ; 160 kPa / 23.2 PSI). CENTRIFUGAL COMPRESSOR - OPERATION For training purposes only © Copyright - TURBOMECA - 2000. 3.21 Edition : December 2000. ENGINE.

(74) Training Manual. ARRIEL 1. COMBUSTION CHAMBER - GENERAL Function. Main components. The combustion chamber forms an enclosure in which the air-fuel mixture is burnt.. - Outer part (front swirl plate and mixer unit) - Inner part (rear swirl plate and shroud). Position. - Fuel injection system. - Central section of the gas generator.. - Turbine casing.. Main characteristics - Type : annular with centrifugal fuel injection - Overall fuel-air ratio : 1/45 - Turbine inlet temperature : 1125 °C (2057 °F).. For training purposes only © Copyright - TURBOMECA - 2000. 3.22 Edition : December 2000. ENGINE.

(75) ARRIEL 1. Training Manual. OUTER PART Front swirl plate. Mixer unit. INNER PART Rear swirl plate. Shroud. Type : Annular with centrifugal fuel injection Overall fuel-air ratio : 1/45 Turbine inlet temperature : 1125 °C (2057 °F). FUEL INJECTION SYSTEM. TURBINE CASING. COMBUSTION CHAMBER - GENERAL For training purposes only © Copyright - TURBOMECA - 2000. 3.23 Edition : December 2000. ENGINE.

(76) Training Manual. ARRIEL 1. COMBUSTION CHAMBER - DESCRIPTION The combustion chamber assembly includes the outer part, the inner part, the turbine casing and the fuel injection system.. Outer part The outer part includes the front swirl plate and the mixer unit. The front swirl plate is provided with calibrated orifices for the passage of primary air ; it is secured to the mixer unit with special rivets. The mixer unit is provided with calibrated orifices for the passage of dilution air ; it is bolted to the rear flange of the turbine casing. It includes the dilution tubes.. Inner part. Turbine casing The casing houses the combustion chamber and the turbine. It has various bosses and, particularly the boss for the combustion chamber drain valve at the bottom of the casing.. Fuel injection system The main fuel injection system includes : the fuel inlet union, the inner fuel tube, the fuel distributor and the centrifugal injection wheel. The injection wheel is mounted by means of curvic couplings between the compressor and the turbine shaft (refer to "FUEL SYSTEM" chapter for further details on the fuel injection system).. The inner part includes the rear swirl plate and the shroud. The rear swirl plate is provided with calibrated orifices for the passage of primary air. The shroud, integral with the rear swirl plate surrounds the shaft ; it is bolted to the turbine nozzle guide vane.. Note : The two parts are made of special alloy. The calibrated orifices are drilled using the electron beam process.. For training purposes only © Copyright - TURBOMECA - 2000. 3.24 Edition : December 2000. ENGINE.

(77) ARRIEL 1. Training Manual. FRONT SWIRL PLATE. TURBINE CASING. DILUTION TUBE MIXER UNIT REAR SWIRL PLATE. REAR SWIRL PLATE SHROUD. SHROUD. MIXER UNIT. Curvic-coupling. Drain valve. FRONT SWIRL PLATE FUEL INJECTION SYSTEM. TURBINE CASING. INJECTION WHEEL. COMBUSTION CHAMBER - DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 3.25 Edition : December 2000. ENGINE.

(78) Training Manual. ARRIEL 1. COMBUSTION CHAMBER - OPERATION The combustion chamber forms an enclosure in which the fuel - air mixture is burnt.. Combustion chamber flow In the combustion chamber, the compressed air is divided into two flows : a primary air flow mixed with the fuel for combustion and a secondary air flow (or dilution air flow) for cooling of the burnt gases.. Secondary air The secondary air (or dilution air) flows through the orifices of the mixer unit and the dilution tubes. It is calibrated to obtain flame stability, cooling of the burnt gases, and distribution of temperature on the turbine. Gas. Primary air. The gas produced by the combustion is directed into the turbine nozzle guide vane.. One part flows through the orifices of the front swirl plate.. Operating parameters. A second part flows through the hollow vanes of the turbine nozzle guide vane (cooling of the vanes) and through the orifices of the rear swirl plate.. The fuel-air ratio for combustion is approximately 1/15 ; the total ratio is approximately 1/45.. The primary air is mixed with the fuel sprayed by the injection wheel. The combustion occurs between the two swirl plates. The flame temperature reaches approximately 2500 °C (4532 °F).. For training purposes only © Copyright - TURBOMECA - 2000. The pressure drop in the combustion chamber is approximately 4 %. The turbine inlet temperature (at design point) is approximately 1125 °C (2057 °F).. 3.26 Edition : December 2000. ENGINE.

(79) ARRIEL 1. Training Manual COMPRESSED AIR (820 kPa / 118.9 PSI ; 320 °C / 608 °F). Primary air (combustion) Secondary air (cooling of burnt gases) Burnt gases. GAS FLOW TO THE TURBINE (1125 °C / 2057 °F). FUEL INJECTION. COMBUSTION (2500 °C / 4532 °F) (pressure loss : 4 %). COMBUSTION CHAMBER - OPERATION For training purposes only © Copyright - TURBOMECA - 2000. 3.27 Edition : December 2000. ENGINE.

(80) Training Manual. ARRIEL 1. GAS GENERATOR TURBINE - GENERAL Function. Main components. The turbine extracts sufficient energy from the gas flow to drive the compressors and the accessories.. - Rotating components (wheels, shafts, bearing). Position. - Stationary components (nozzle guide vanes, containment shield, casing).. - At the rear of the gas generator.. Main characteristics - Type : two stage axial - Turbine inlet temperature : 1125 °C (2057 °F) - Turbine outlet temperature : 880 °C (1616 °F) - N1 speed ≈ 52000 RPM (100 %) ACW. For training purposes only © Copyright - TURBOMECA - 2000. 3.28 Edition : December 2000. ENGINE.

(81) ARRIEL 1. Training Manual. NOZZLE GUIDE VANES. WHEELS. BEARING. Type : Two stage axial Turbine inlet temperature : 1125 °C (2057 °F) Turbine outlet temperature : 880 °C (1616 °F) N1 speed 52000 RPM (100%) ACW. CONTAINMENT SHIELD. CASING. SHAFTS. GAS GENERATOR TURBINE - GENERAL For training purposes only © Copyright - TURBOMECA - 2000. 3.29 Edition : December 2000. ENGINE.

(82) Training Manual. ARRIEL 1. GAS GENERATOR TURBINE DESCRIPTION The gas generator turbine assembly includes rotating components and stationary components.. The stationary components are the turbine nozzle guide vanes, the containment shield, the turbine casing and the diffuser casing.. Rotating components The main rotating components are the turbine wheels. The wheels consist of either a disc and fir-tree mounted blades or blades cut from the solid. The front wheel is coupled by curvic-couplings to the turbine shaft and to the second stage wheel. The rear wheel is coupled to a stub shaft by a curvic-coupling. The stub shaft is supported by a roller bearing. Rotating labyrinths provide sealing. A tie-bolt secures the rotating assembly.. For training purposes only © Copyright - TURBOMECA - 2000. Stationary components. The first stage nozzle guide vane includes a row of hollow vanes. It is mounted on the combustion chamber. The second stage nozzle guide vane includes a row of vanes mounted in a ring. The containment shield provides containment in case of blade failure. The turbine casing forms the housing of turbines and combustion chamber. The diffuser casing connects the gas generator and the power turbine and its hub contains the housing for the gas generator rear bearing. At the rear it houses the power turbine nozzle guide vane.. 3.30 Edition : December 2000. ENGINE.

(83) ARRIEL 1. Training Manual NOZZLE GUIDE VANES. TURBINE SHROUD. TURBINE WHEELS. DIFFUSER CASING. TURBINE CONTAINMENT SHIELD 2nd STAGE TURBINE WHEEL. BEARING (roller). 1st STAGE TURBINE WHEEL TURBINE SHROUD. TIE-BOLT. DIFFUSER CASING 2nd STAGE NOZZLE GUIDE VANE. REAR SHAFT 1st STAGE NOZZLE GUIDE VANE FRONT SHAFT FRONT SHAFT. TURBINE CASING. CONTAINMENT SHIELD. Curvic-coupling. GAS GENERATOR TURBINE - DESCRIPTION For training purposes only © Copyright - TURBOMECA - 2000. 3.31 Edition : December 2000. ENGINE.

(84) Training Manual. ARRIEL 1. GAS GENERATOR TURBINE - OPERATION The gas generator turbine transforms the gas energy into mechanical power to drive the compressors and various accessories.. Operating parameters. The operation is characterized by the first phase of expansion.. - Turbine inlet temperature : 1125 °C (2057 °F). The operation is characterised by the following parameters :. - Turbine outlet temperature : 880 °C (1616 °F). Turbine gas flow The burnt gases first flow through the nozzle guide vanes. The gas velocity increases due to the convergent passage. The flow on the blades results in aerodynamic forces whose resultant causes the rotation of the wheel. The gases, still containing energy, are directed to the power turbine.. For training purposes only © Copyright - TURBOMECA - 2000. 3.32 Edition : December 2000. ENGINE.

(85) Training Manual. GAS FROM THE COMBUSTION CHAMBER (1125 °C / 2057 °F). ARRIEL 1. GAS EXPANSION IN THE NOZZLE GUIDE VANE (convergent passage). ROTATION Rotation. Nozzle guide vane. COMPRESSOR DRIVE (52000 RPM ; ACW 800 kW ; 1072 Shp). Turbine wheel. GAS TO THE POWER TURBINE (880 °C / 1616 °F). GAS GENERATOR TURBINE - OPERATION For training purposes only © Copyright - TURBOMECA - 2000. 3.33 Edition : December 2000. ENGINE.

(86) Training Manual. ARRIEL 1. POWER TURBINE - GENERAL Function. Main components. The turbine extracts the energy from the gas to drive the power shaft through the reduction gearbox.. - Rotating components (wheel, shaft, bearings) - Stationary components (nozzle guide vane, containment shield, casing).. Position - Between the gas generator and the reduction gearbox. It forms the module M04.. Main characteristics - Type : axial, single-stage - Turbine inlet temperature : 880 °C (1616 °F) - Turbine outlet temperature : 600 °C (1080 °F) - N2 speed at 100 % ≈ 41586 RPM, CW. For training purposes only © Copyright - TURBOMECA - 2000. 3.34 Edition : December 2000. ENGINE.

(87) ARRIEL 1. Training Manual NOZZLE GUIDE VANE. WHEEL. BEARINGS. Type : Axial, single stage Turbine inlet temperature : 880 °C (1616 °F) Turbine outlet temperature : 600 °C (1080 °F) N2 speed at 100% ≈ 41586 RPM (CW). CONTAINMENT SHIELD. POWER TURBINE CASING. SHAFT. POWER TURBINE - GENERAL For training purposes only © Copyright - TURBOMECA - 2000. 3.35 Edition : December 2000. ENGINE.

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