scholarly journals Calculation of a 3D turbulent flow in aircraft gas turbine engine ducts

2020 ◽  
Vol 2020 (4) ◽  
pp. 65-71
Author(s):  
Yu.A. Kvasha ◽  
Keyword(s):  
Numerical Simulation ◽  
Turbulent Flow ◽  
Gas Turbine ◽  
Gas Flow ◽  
Turbine Engines ◽  
Gas Flows ◽  
Gas Turbine Engines ◽  
Compressor Inlet ◽  
Air Intake ◽  
Engine Compressor

This work is devoted to the development of approaches to the numerical simulation of 3D turbulent gas flows in different ducts of aircraft gas turbine engines, in particular in inlet device ducts. Inlet devices must provide large values of the total pressure recovery factor and flow uniformity at the engine compressor inlet. The aim of this work is the verification of the operability of a technique developed earlier for the calculation of the parameters of a 3D turbulent flow in complex-shape ducts. The basic approach is a numerical simulation of 3D turbulent gas flows on the basis of the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. The proposed technique of numerical simulation of a 3D gas flow was tested by calculating a 3D laminar flow in a square pipe bent at a right angle. The calculated flow pattern is in satisfactory agreement with the experimental data on the flow structure in a pipe elbow reported in the literature. Based on a numerical simulation of a 3D turbulent flow in the air duct of one of the air intake configurations for an aircraft turboprop engine, the efficiency of that configuration is assessed. The calculated flow parameter nonuniformity at the air intake outlet, i. e., at the compressor inlet, is compared with that obtained earlier for another air intake configuration for the same engine. It is pointed out that the air intake configuration considered earlier provides a much more uniform flow parameter distribution at the engine compressor inlet. On the whole, this work shows that the quality of subsonic air intakes for aircraft gas turbine engines can be assessed using the proposed numerical technique of 3D gas flow simulation. The results obtained may be used in the aerodynamic improvement of inlet devices for aircraft engines of different types.

Internally Generated Noise From Gas Turbine Engines. Measurement and Prediction

1967 ◽  
Vol 89 (2) ◽  
pp. 177-185 ◽  
Author(s):  
M. J. T. Smith ◽  
M. E. House
Keyword(s):  
Gas Turbine ◽  
Full Scale ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Radiation Patterns ◽  
Noise Sources ◽  
Prediction Technique ◽  
Noise Measurements ◽  
Engine Compressor

The noise sources from gas turbine engines are defined and their radiation patterns identified from test results. Examination of single-stage and full-scale engine compressor noise measurements leads to a prediction technique being evolved for inlet and efflux levels.

Problems and Use of the Scaling Factors in the Numerical Simulation of Jet Engines

1990 ◽  
Author(s):  
G. Torella
Keyword(s):  
Numerical Simulation ◽  
Trend Analysis ◽  
Gas Turbine ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Jet Engines ◽  
Scaling Factors ◽  
Operational Life

The possibility of the use of scaling factors in the calculations and in the simulation of gas turbine engines have been considered. Application of this technique to the simulation of trend analysis, the evaluation of the component maps shifting during the operational life of the engine and the calculation of matrices of influence have been presented. Moreover, some problems related to the use of scaling factors have been studied and their effects on the engine performance have been presented.

Techniques and Methods to Improve the Dynamic Strength of Gas Turbine Engines Compressor Rotor Wheels

2014 ◽  
Author(s):  
Daria Kolmakova ◽  
Grigorii Popov ◽  
Aleksandr Shklovets ◽  
Aleksandr Ermakov
Keyword(s):  
Gas Turbine ◽  
Calculation Method ◽  
Gas Flow ◽  
Dynamic Strength ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Cfd Model ◽  
Compressor Blades ◽  
Compressor Rotor ◽  
Pressure Compressor

The approaches to reducing the alternating stresses in the compressor blades, arising at a resonance, are discussed in paper. Maximum alternating stresses in blades of the fifth stage of intermediate pressure compressor (IPC, that operating under the gas flow circumferential variation conditions, are defined on the basis of the forced blade oscillations calculation method. Parametric CFD-model which allows to introduce different stagger angles and circumferentially alternating blade pitch at the guide vanes of IPC fifth stage was created to reduce the stresses. The flow circumferential variation was reduced by changing these parameters and as a consequence the resonant stresses were decreased by more than 2.5 times.

scholarly journals Why an Engine Air Particle Separator (EAPS)?

1990 ◽  
Author(s):  
Joe Thomas Potts
Keyword(s):  
Gas Turbine ◽  
Volcanic Ash ◽  
Vortex Generator ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Test Results ◽  
Turbine Engine ◽  
Industrial Pollutants ◽  
Air Intake ◽  
Particle Separator

The purpose of this technical paper is to describe how an Engine Air Particle Separator (EAPS) removes contaminant particles before they enter the gas turbine engine. Gas turbine engines perform poorly in air containing sand, volcanic ash, industrial pollutants, etc. Typical dirt related gas turbine malfunctions include: • Erosion of the engine and air cycle machinery rotating components. • Clogging and fouling of turbine section. • Wear of oil wetted components caused by contaminated lubricants. Contaminated air entering an EAPS is sent through a swirling motion induced by the vortex generator. This swirling motion causes the heavier dirt particles and water droplets to be thrown radially outward by centrifugal force so that they may be scavenged from the engine air intake. This report will provide test results of helicopters with and without EAPS and describes the steps necessary to design an EAPS for various air vehicles and engines.

scholarly journals Design and development of combustion chambers for gas turbine engines based on calculations of various levels of complexity

2021 ◽  
Vol 20 (3) ◽  
pp. 7-23
Author(s):  
Y. B. Aleksandrov ◽  
T. D. Nguyen ◽  
B. G. Mingazov
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Flow ◽  
Combustion Process ◽  
Three Dimensional ◽  
Numerical Calculations ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Combustion Chambers ◽  
Flame Tube

The article proposes a method for designing combustion chambers for gas turbine engines based on a combination of the use of calculations in a one-dimensional and three-dimensional formulation of the problem. This technique allows you to quickly design at the initial stage of creating and development of the existing combustion chambers using simplified calculation algorithms. At the final stage, detailed calculations are carried out using three-dimensional numerical calculations. The method includes hydraulic calculations, on the basis of which the distribution of the air flow passing through the main elements of the combustion chamber is determined. Then, the mixing of the gas flow downstream of the flame tube head and the air passing through the holes in the flame tube is determined. The mixing quality determines the distribution of local mixture compositions along the length of the flame tube. The calculation of the combustion process is carried out with the determination of the combustion efficiency, temperature, concentrations of harmful substances and other parameters. The proposed method is tested drawing on the example of a combustion chamber of the cannular type. The results of numerical calculations, experimental data and values obtained using the proposed method for various operating modes of the engine are compared.

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