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A Research Paper on Analysis of De Laval Nozzle on Ansys Workbench

A Research Paper on Analysis of De Laval Nozzle on Ansys Workbench

The combustion chamber in which fluid present the convergent section of De Laval Nozzle is connected to it. In this section the fluid gains the kinetic energy and loosed pressure energy due to Bernoulli’s principle and the law of conservation of mass. The acceleration of fluid takes places from convergent to throat section. As the force of incoming flow is greater than throat mass flow rate, the rate of flow from the convergent section increases rapidly. The throat section is present between convergent and divergent section its smallest in size as compare both section. This section reason of change in velocity in engine. To provide subsonic flow (0<M<1), Supersonic flow, Sonic flow, the increase in velocity of fluid is directly proportional to decrease in area of the duct. [5-6]

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CFD Analysis of De Laval Nozzle Geometry & Effect of Gas Pressure Variation at the Entrance

CFD Analysis of De Laval Nozzle Geometry & Effect of Gas Pressure Variation at the Entrance

Abstract: De Laval nozzle is a converging-diverging nozzle which has the ability to convert the chemical energy with high pressure into kinetic energy with high velocity and low pressure. The scheme of change of speed and pressure within the nozzle depends on the change of the cross-section area of the nozzle. The nozzle is used in jet engines. This study is concerned with the study of the performance of the work of de Laval nozzle, two models were designed; the first model: when the total pressure (gauge) of air at the entrance is equal to 9 bar and the second model: at the total pressure (gauge) of the entrance is equal to 11 bar. The total pressure in the two models was decreased, and the change in the Mach number was observed at the outlet of the De Laval nozzle. The models were designed and analyzed in the ANSYS Fluent program. The total air pressure changes at the nozzle entrance and their effect on changing the Mach number at the exit were studied. The results obtained from the ANSYS Fluent program were compared with the theories of gas dynamics.

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A Theoretical Mass Transfer Approach for Prediction of Droplets Growth Inside Supersonic Laval Nozzle

A Theoretical Mass Transfer Approach for Prediction of Droplets Growth Inside Supersonic Laval Nozzle

Numerous empirical correlations are presented in the literature for prediction of liquid droplet growth rate and the corresponding temperature during condensation of a pure component (steam) inside a Laval nozzle. Various combinations of these correlations can be used to simulate the nucleation and growth processes inside a supersonic nozzle. Different combinations of empirical correlations show almost the same performances on prediction of pressure ratio distributions along various nozzles. On the other hand, some combinations perform more adequately estimation of mean droplet radius profile along the Laval nozzles.

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A Research Paper on Analysis of De Laval Nozzle on Ansys Workbench

A Research Paper on Analysis of De Laval Nozzle on Ansys Workbench

The combustion chamber in which fluid present the convergent section of De Laval Nozzle is connected to it. In this section the fluid gains the kinetic energy and loosed pressure energy due to Bernoulli’s principle and the law of conservation of mass. The acceleration of fluid takes places from convergent to throat section. As the force of incoming flow is greater than throat mass flow rate, the rate of flow from the convergent section increases rapidly. The throat section is present between convergent and divergent section its smallest in size as compare both section. This section reason of change in velocity in engine. To provide subsonic flow (0<M<1), Supersonic flow, Sonic flow, the increase in velocity of fluid is directly proportional to decrease in area of the duct. [5-6]

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Movement Analysis of a Fluid through a Laval Nozzle Axial Symmetry with Fluent Program

Movement Analysis of a Fluid through a Laval Nozzle Axial Symmetry with Fluent Program

The purpose of the paper is to present the form of partial differential equations in analysis of usage for the transition from subsonic to supersonic by Laval nozzle and using Fluent program to determine the variation of parameters features two-dimensional movement.

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Pulsed Laval nozzle study of the kinetics of OH with unsaturated hydrocarbons at very low temperatures

Pulsed Laval nozzle study of the kinetics of OH with unsaturated hydrocarbons at very low temperatures

pumps are providing a background pressure close to that required for a stable flow. The oscillations may indicate the presence of oblique shocks at the nozzle exit rather than a normal shock wave, which is perpendicular to the gas flow. Further discussion of this point can be found in ref. 24 Beyond

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Intensification of Heat Transfer Processes in the Low Temperature Short Heat Pipes with Laval Nozzle Formed Vapour Channel

Intensification of Heat Transfer Processes in the Low Temperature Short Heat Pipes with Laval Nozzle Formed Vapour Channel

Abstract: The results of flow studies of moist vapour in Laval-liked vapour channels of short linear heat pipes (HPs) are presented. The increase in heat transfer coefficient of short linear HPs, intended for creation the cooling systems of heat- stressed designs of spacecraft is carried out by making the HPs vapour channel forms of the Laval-liked nozzle. Comparison of the heat transfer coefficients of short HPs with the standard cylindrical vapour channel and the channel, made in the Laval nozzle form with the equality of all dimensions, flat evaporator shows that the HPs with the Laval-liked nozzle vapour channel exceeds the heat transfer characteristics of the standard HPs with a cylindrical vapour channel under high thermal loads. The study of the flow and condensation in such shaped vapour channels of the short HPs at high thermal loads gives an opportunity to analyze in detail the advantages of using such HPs. Capacitive sensors are additionally installed in cooled top covers of the HPs, and electromagnetic pulses with a frequency of 100 kHz were supplied to them from the external generator. At heating the HPs evaporator, starting from a certain thermal power threshold value, electromagnetic pulses became modulated. It is related with the formations of the boiling process in the capillary-porous evaporator and large amount of vapour over it and its discontinuous distribution. An analytical and numerical evaluation are applied to study the duration of the occurring pulsations, and the analytical results are compared with numerical and experimentally obtained values of the pulsations periods.

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Parameters Calculation Algorithm for Shock Waves of a Normal Laval Nozzle

Parameters Calculation Algorithm for Shock Waves of a Normal Laval Nozzle

A shock wave is a disturbance that propagates through a solid, liquid, gas, and in some cases by vacuum through a field such as electromagnetic and transport energy. Shock waves are characterized by a sudden, almost discontinuous environmental characteristics. Under certain conditions, in the supersonic nozzle divergent a normal shock wave can be stabilized. The shock wave is normal to the direction of movement. The fluid passing stationary shock wave parameters suddenly change their status.

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Low temperature studies of the removal reactions of<sup>1</sup>CH<inf>2</inf>with particular relevance to the atmosphere of Titan

Low temperature studies of the removal reactions of<sup>1</sup>CH<inf>2</inf>with particular relevance to the atmosphere of Titan

voir via two pulsed solenoid valves (Parker 9 Series), fired at a 5 Hz repetition frequency with a pulse duration of between 10 and 20 ms, depending on the Laval nozzle employed. The gas mix- ture was then expanded through the convergent-divergent shaped Laval nozzle into a low pressure stainless steel cylindrical chamber (774 mm length × 240 mm diameter), producing a thermally equili- brated, low temperature jet. The temperature and density profile of the jet were characterized by impact pressure measurements, and the temperature also by rotationally resolved laser-induced fluores- cence spectroscopy. The properties of the characterized expansions used in this study are given in Table 1 .

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Rainbow schlieren measurements in underexpanded jets from square supersonic micro nozzles

Rainbow schlieren measurements in underexpanded jets from square supersonic micro nozzles

Three-dimensional density fields of the shock containing free jet issued from a square Laval nozzle with a design Mach number of 1.5 were quantitatively obtained by the rainbow schlieren deflectometry combined with the computed tomography based on the convolution backprojection algorithm. As a result, it was found that a density contour plot at any cross-section of the jet can be efficiently inferred from the schlieren CT. Density fields reconstructed from the schlieren CT are in good quantitative agreement with those from vortex sheet model.

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Gas Dynamics Algorithms applied to the Analysis of Fluid Subsonic and Supersonic Movement through the Laval Nozzles

Gas Dynamics Algorithms applied to the Analysis of Fluid Subsonic and Supersonic Movement through the Laval Nozzles

ABSTRACT: The convergent or convergent – divergent nozzle are often used in gas-dynamic technique. The study of these nozzles is complex and it requires complex mathematical models. The paper generates a Laval nozzle contour model 1 for critical diameter of 20 mm, that are known angle of convergence q 1 , divergence angle q 2 and end point abscissa. Using gas dynamic functions determine ideal f luid motion parameters Laval nozzle in the convergence and divergence. The stagnation pressure is p 0  6.10 P a 6 and the stagnation temperature T 0  600 K . Supersonic air flow inside Laval nozzle is model using Fluent software.

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NUMERICAL SIMULATION ON CONDENSING FLOW OF WATER VAPOR OF WET NATURAL GAS INSIDE THE NOZZLE

NUMERICAL SIMULATION ON CONDENSING FLOW OF WATER VAPOR OF WET NATURAL GAS INSIDE THE NOZZLE

Supersonic cyclone separator is the device that realizes the separation of gas and liquid by condensing with temperature decreased when the wet natural gas flows through the Laval nozzle. The core of supersonic hydrocyclone separation technology of wet gas is to use the low temperature and low pressure condition to condense water and heavy hydrocarbons. In 1942, Oswatisch (Ding et al., 2014) carried out a one-dimensional numerical simulation of the condensation flow of the wet steam in the Laval nozzle, and the simulated results were in good agreement with the experimental data. However, it is relatively late to use supersonic cyclone to separate the gas and liquid (Hill, 1966; Holten et al., 2005; Cao et al., 2008). The wet gas is at low temperature and low pressure condition through the expansion after getting into the Laval nozzle, and reaches sound velocity at the throat position, which increases supercooling and supersaturation, when the supercooling degree reaches to a certain level, condensation occurs. To effectively separate water vapor and heavy hydrocarbon, it must ensure that the droplet radius of Laval nozzle at the outlet is within a certain range. If the droplet radius is too small, the droplets will go downstream with gas, on the contrary it will affect the cyclone effect as its large inertia force.

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Design of a test facility for probe calibration

Design of a test facility for probe calibration

Abstract. A possibility to easily calibrate probes for flow field measurements is always welcome. From this reason, a design of a test facility for probe calibration was made. The probes will be calibrated in a free jet of known properties, which is created by an exchangeable nozzle to cover a wide range of Mach numbers up to Mach 2. The most important is to create a homogeneous flow across the test section. This is accomplished by a precise design of the nozzles carried out by numerical tools. The convergent nozzle part is common for all subsonic flow regimes while the divergent part (forming a de Laval nozzle) is suited for a specific supersonic Mach number. These parts are designed using the method of characteristics. Numerical simulations performed by a CFD code show a feasibility and quality of the proposed test facility.

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Designing and prototyping a small scale steam driven jet pump

Designing and prototyping a small scale steam driven jet pump

For the steam nozzle the most important parameter is the exit static pres- sure. This pressure must be below 1 bar in order to draw water out of the water tank, as said before. Figure 2.3 shows the relation between the Mach number and the pressure ratio of the converging nozzle.This is the rela- tion between the existing total pressure and the maximum obtainable static pressure. From the Hugionot relations it can be obtained that the maximum Mach number can at most equal to 1. When M = 1 the area change is equal to zero. Resulting in a maximum pressure ratio of 0.5774 at the the throat( the area change is zero, so M must be equal to 1.) This means, With the given stagnation conditions, that a suction pressure at the end of the nozzle never can be achieved using only a converging nozzle. therefore, a ’De laval nozzle’ has to be used in order to achieve the desired pressure ratio. In or-

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A Study on Performance Improvement of Low Pressure Injection Type Ejector Using CFD Simulation

A Study on Performance Improvement of Low Pressure Injection Type Ejector Using CFD Simulation

Abstract - Ejector is a kind of pump that is a mechanical device that sucks in the second fluid and transfers it by using the pressure energy of high pressure fluid. In this paper, we investigated the effect of nozzle shape on the performance of ejector using CFD analysis based on finite volume method. The optimal conditions for the best sucking of the suction fluid influencing the performance of ejector were investigated by varying the nozzle diameter in the mixing chamber, the nozzle neck length, and the distance from the nozzle tip to the diffuser inlet where the fluid exits to the outside. As a result of the study, the performance of the ejector was found to be affected by the diameter and shape of the nozzle. As the diameter of the nozzle inside the mixing chamber decreases, the mixing ratio increases and the mixing ratio decreases as the nozzle diameter increases. On the other hand, the influence of the nozzle neck length, the nozzle tip, and the distance to the diffuser inlet was found to be insignificant. As the final shape of the ejector was increased, the target flow rate increased proportionally and no backflow phenomenon was found. Also, as the diameter increases, the required pressure also decreases proportionally, and it is considered that the performance as ejector for low pressure transfer can be satisfied.

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Design Evalution and Optimization of Nozzle Used in Diesel Engine Fuel Injector

Design Evalution and Optimization of Nozzle Used in Diesel Engine Fuel Injector

ABSTRACT: The nozzle is used to convert the chemical thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the low velocity, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and temperature. Nozzle is a device designed to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the stream that exhaust from them. Nozzles come in a variety of shapes and sizes depending on the mission of the rocket, this is very important for the understanding of the performance characteristics of rocket. Convergent divergent nozzle is the most commonly used nozzle since in using it the propellant can be heated in combustion chamber. In this thesis the convergent divergent nozzle changing the different nozzle diameters and different fluids at different velocities. We modeled convergent divergent nozzle changing with different nozzle diameters and Analyzed the convergent divergent nozzle with different mass flow rates to determine the pressure drop, heat transfer coefficient, and velocity and heat transfer rate for the fluid by CFD technique.

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International Journal of Emerging Technology and Advanced Engineering Website: www.ijetae.com (ISSN 2250-2459, ISO 9001:2008 Certified Journal Volume 7, Issue 10, October 2017)

International Journal of Emerging Technology and Advanced Engineering Website: www.ijetae.com (ISSN 2250-2459, ISO 9001:2008 Certified Journal Volume 7, Issue 10, October 2017)

Now as the pressure is increased at the inlet of the control volume the pressure contour as shown in the fig 6 is increased at rotor blade inlet to1.2 bar and the velocity at nozzle out let is more than 570m/s as shown in the fig 7

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Experimental Investigation on Comparison of Local Nusselt Number Using Twin Jet Impingement Mechanism

Experimental Investigation on Comparison of Local Nusselt Number Using Twin Jet Impingement Mechanism

The transient heat-transfer characteristics on a flat plate using circular air-jet impingement were studied by [6]. The local Nu number rapidly increases when the air jet begins its impingement. The increase in Nu speed slows down as the impinging jet continues to cool down at the 50–80 s region. Furthermore, [22] studied the heat transfer and fluid flow of a slot jet impingement with a small nozzle-to-plate spacing in which a secondary peak in the Nu number was observed. The results showed that the mean velocity profile in the stagnation point swerved from the standard law of the wall. The Nu

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Mathematical Model for the Injector of a Common Rail Fuel Injection System

Mathematical Model for the Injector of a Common Rail Fuel Injection System

When calculating pressure p and velocity w of the fuel, we apply the Allevi theory [1]. It can be assumed that the fluid only flows one way—in the direction of the pipe—because of the small diameter of the nozzle channel compared to its length. All frictional losses of fluid in the nozzle channel are neglected, because the nozzle channel is relatively short. The equations depicting the velocity and pressure at any point between cross sections III and IV are

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VORTEX TUBE REFRIGERATION: A REVIEW

VORTEX TUBE REFRIGERATION: A REVIEW

From the study of above literature it is revealed that the maximum research done by changing the various parameter like diameter of nozzle, diameter of orifice, angle of conical valve, diameter of vortex tube, length of vortex tube, L/D ratio and pressure difference. There is need to give attention towards different materials by knowing the thermal conductivity, bulk strength. With the help of these parameters we may lead maximum temperature difference in between hot air stream and cold air stream. The optimum results are obtained with inlet pressure of 5 bars, conical angle in between 45 0 to 90 0 , diameter of nozzle of 2.969 mm, diameter of orifice of 5 mm, and such as L/D ratio. This results in increasing the efficiency of vortex tube refrigeration. Hence, vortex tube can be used for any type of spot cooling or spot heating application.

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