Ms6001b operation description

(1)

MS 6001

(2)

2 / GE / February 11, 2010 0 500 1,000 1,500 2,000 2,500 3,000 3,500 0 50,000 100,000 150,000 200,000 250,000 Fired Hours Fi re d St ar ts Cyclic Duty Peaking Duty Base Load

• 42 MW… 50/60 Hz

• Launched in 1978

• Over 1000 units

• Over 47 million operating hours

• Wide range of applications

• 99% reliability… 97% availability

• 12,000 hours of continuous operation

• Fuel flexible… from refinery gases to

crude oil

• Low NOx emissions 15ppm

(3)

6B evolution… 30 % increase in output

30

32

34

36

38

40

42

44

19

78

19

78

19

81

19

83

19

87

19

95

19

97

19

99 MW

(4)

4 / GE / February 11, 2010

(5)

6B Simple cycle performances

Output (MW):

42.1 Efficiency (%):

32.1 Heat rate (kj/kwh):

11,230

Pressure ratio

11.8 Firing temperature (°C):

1,140

Shaft speed (rpm):

5,163

Exhaust flow (KG/sec):

141.1 Exhaust temperature (°C):

548

ISO conditions - natural gas

(6)

6 / GE / February 11, 2010

• Hot end drive

• 2 bearings

Not to scale

• Axial flow exhaust

• High performance

6B Design Features

• Axial compressor

• 17 stages

• IGV

• Bolted construction

• 3 stage turbine

• Bolted construction

• Advanced materials

• Enhanced cooling

• 10 can annular chambers

• Dual fuel capability

• 15 ppm NOx

(7)

(8)

8 / GE / February 11, 2010

(9)

6B Typical layout

Exhaust stack

Generator

Accessories

Gas turbine

Turbine control

compartment

Inlet filter

(10)

10 / GE / February 11, 2010

6B – Turbine support

The base that supports the gas turbine is

a structural steel fabrication of welded

(11)

(12)

12 / GE / February 11, 2010

6B – Inlet Casing

The inner bellmouth is

positioned to the outer

bellmouth by seven

airfoil-shaped radial struts and

seven axial tiebars

(13)

(14)

14 / GE / February 11, 2010

(15)

LVDT

MOOG

Axial Compressor IGV

(16)

16 / GE / February 11, 2010

(17)

(18)

18 / GE / February 11, 2010

(19)

Feature:

stages 17

stage of IGV (variable) 1

stages of EGV 2

Pressure Ratio: 11,8

AIR FLOW (KG/sec): 140

SPEED (rpm): 5163

Material:

Stub Shaft NiCrMoV

Compressor Disc NiCrMoV (stg. 1-15)

CrMoV (stg. 16-17)

IGV GTD 450

Blade C 450 (stg. 1-8)

AISI 403 (stg.9-17)

(20)

20 / GE / February 11, 2010

(21)

(22)

22 / GE / February 11, 2010

(23)

6B – Compressor Casing

The compressor stator

blade are mounted into

ring segments in the first

The remaining stages have a square

base dovetail and are inserted directly

into circumferential grooves in the

(24)

24 / GE / February 11, 2010

6B – Extraction pockets

• Compressor discharge casing… bleed belt incorporated into casting

• Extraction system pipework

• Turbine casing… bosses for pipe flange attachment

• Second stage nozzle with radiation shield

(25)

(26)

26 / GE / February 11, 2010

Feature:

N° chamber 10

Type reverse flow

Burner single, dual fuel

Firing Temperature (°C) + 1100

Water injection available

Steam injection available

DLN available

Material:

Liner Hastelloy X + HS188

with Thermal barrier coating

Cap Hastelloy X + HS188

Crossfire Tube AISI 304

Transition piece Nimonic 263

with Thermal barrier coating

(27)

6B – C.C. Typical Layout

Spark Plug

(28)

28 / GE / February 11, 2010

(29)

• Proven Dry Low NOx design and experience…

–Gas 15 ppm NO

_x

(15%, O

₂

)

–Distillate 42 ppm NO

_x

(15%, O

₂

) with water injection

(30)

30 / GE / February 11, 2010

Reaction zone

Where the fuel is burned with the combustion air

Dilution zone

Where additional air is mixed with the hot combustion gases

Liner Cap

Metering holes at enter of air

Louver

provide a film of air for cooling the walls of the liner and cap

(31)

(32)

32 / GE / February 11, 2010

(33)

(34)

34 / GE / February 11, 2010

(35)

(36)

36 / GE / February 11, 2010 Feature: stages 3 Ratation counterclockwise

Type axial flow

SPEED (rpm): 5163

Material:

Stub Shaft CrMoV

Turbine Disc CrMoV

Nozzle 1°stg FSX 414 Bucket 1°stg GTD111 Nozzle 2°stg GTD222 Bucket 2°stg IN 738 Nozzle 3°stg GTD222 Bucket 3°stg IN 738

6B – Turbine Rotor

(37)

1° Wheel Turbine

2° Wheel Turbine

Spacer

3° Wheel Turbine

(38)

38 / GE / February 11, 2010

• Use existing GTD111DS material…

Nickel base alloy material and coating

technology

• Turbine aerodynamic analysis…

New engine operating conditions

• Optimised cooling configuration…

16 cooling holes

(39)

(40)

40 / GE / February 11, 2010

• Nickel base alloy material

• Enhanced cooling of airfoil

• Contoured tip shroud for creep life improvement

(41)

(42)

42 / GE / February 11, 2010

• Use existing FSX414 material (cobalt base alloy)

• Enhanced cooling of platforms

• Improved leakage control with introduction of chordal

hinge and additional line seal

(43)

Second Stage Nozzle

Third Stage

Nozzle

Use existing GTD222… nickel base alloy material

and coating technology

(44)

44 / GE / February 11, 2010

(45)

(46)

46 / GE / February 11, 2010

(47)

(48)

48 / GE / February 11, 2010

(49)

The gas turbine unit contains two main journal bearings used to support the gas turbine rotor. The unit also includes thrust bearings to maintain the rotor-to-stator axial position. These bearings and seals are incorporated in two housings: one at the inlet and one in the exhaust frame. These main bearings are pressure lubricated by fluid supplied from the main lubricating system. The fluid flows through branch lines to an inlet in each bearing housing.

No. Class Type

1 Journal Elliptical

2 Journal Elliptical

1 Thrust Load (Equalizing)

1 Thrust Unloaded (Non-Equalizing)

(50)

50 / GE / February 11, 2010

(51)

(52)

52 / GE / February 11, 2010

(53)