THE MATHEMATICAL MODELLING OF THE THREE-DIMENSIONAL NONSTATIONARY NONLINEAR TEMPERATURE FIELDS OF GAS-TURBINE ENGINE BLADES

1994 ◽  
Author(s):  
V. M. Epifanov ◽  
V. Stankiewitcz
Keyword(s):  
Mathematical Modelling ◽  
Gas Turbine ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Temperature Fields ◽  
Turbine Engine ◽  
Nonlinear Temperature

Gas Turbine Engine Test Cell Modeling

1990 ◽  
Author(s):  
D. Salinas ◽  
E. E. Cooper
Keyword(s):  
Kinetic Energy ◽  
Gas Turbine ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Test Cell ◽  
Dimensional System ◽  
Engine Test ◽  
Turbine Engine ◽  
Coordinate Model ◽  
Cartesian Coordinate

A numerical simulation of the aerothermal characteristics of a gas turbine engine test cell is presented. The three-dimensional system is modeled using the PHOENICS computational fluid dynamics code. Results predict the velocity field, temperatures, pressures, kinetic energy of turbulence, and dissipation rates of turbulent kinetic energy. Numerical results from two versions, a cartesian coordinate model and a body fitted coordinate model, are compared to experimental data. The comparison shows good quantitative and very good qualitative agreement, suggesting that numerical modeling would be useful in the preliminary design of gas turbine test facilities.

Blade Erosion in Automotive Gas Turbine Engine

1995 ◽  
Vol 117 (1) ◽  
pp. 213-219 ◽  
Author(s):  
M. Metwally ◽  
W. Tabakoff ◽  
A. Hamed
Keyword(s):  
Gas Turbine ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Particulate Flow ◽  
Particle Impact ◽  
Surface Erosion ◽  
Blade Surface ◽  
Erosion Model ◽  
Turbine Engine ◽  
Automotive Engine

In this work, a study has been conducted to predict blade erosion and surface deterioration of the free power turbine of an automotive gas turbine engine. The blade material erosion model is based on three-dimensional particle trajectory simulations in the three-dimensional turbine flow field. The particle rebound characteristics after surface impacts were determined from experimental measurements of restitution ratios for blade material samples in a particulate flow tunnel. The trajectories provide the spatial distribution of the particle impact parameters over the blade surfaces. A semi-empirical erosion model, derived from erosion tests of material samples at different particulate flow conditions, is used in the prediction of blade surface erosion based on the trajectory impact data. The results are presented for the three-dimensional particle trajectories through the turbine blade passages, the particle impact locations, blade surface erosion pattern, and the associated erosion parameters. These parameters include impact velocity, impact angle, and impact frequency. The data can be used for life prediction and performance deterioration of the automotive engine under investigation.

scholarly journals Assessment of Mechanical Design Parameters for an Aero Gas Turbine Engine Jet Pipe Casing using Finite Element Analysis

2020 ◽  
Vol 9 (5) ◽  
pp. 1197-1201
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Gas Turbine ◽  
Mechanical Design ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Element Analysis ◽  
Engine Operation ◽  
Turbine Engine

Aero Gas Turbine engines power aircrafts for civil transport application as well as for military fighter jets. Jet pipe casing assembly is one of the critical components of such an Aero Gas Turbine engine. The objective of the casing is to carry out the required aerodynamic performance with a simultaneous structural performance. The Jet pipe casing assembly located in the rear end of the engine would, in case of fighter jet, consist of an After Burner also called as reheater which is used for thrust augmentation to meet the critical additional thrust requirement as demanded by the combat environment in the war field. The combustion volume for the After burner operation together with the aerodynamic conditions in terms of pressure, temperature and optimum air velocity is provided by the Jet pipe casing. While meeting the aerodynamic requirements, the casing is also expected to meet the structural requirements. The casing carries a Convergent-Divergent Nozzle in the downstream side (at the rear end) and in the upstream side the casing is attached with a rear mount ring which is an interface between engine and the airframe. The mechanical design parameters involving Strength reserve factors, Fatigue Life, Natural Frequencies along with buckling strength margins are assessed while the Jet pipe casing delivers the aerodynamic outputs during the engine operation. A three dimensional non linear Finite Element analysis of the Jet pipe casing assembly is carried out, considering the up & down stream aerodynamics together with the mechanical boundary conditions in order to assess the Mechanical design parameters.

THERMO ACOUSTIC PROCESSES IN LOW EMISSION COMBUSTION CHAMBER OF GAS TURBINE ENGINE CAPACITY 25 MW

2019 ◽  
pp. 86-90
Author(s):  
Sergey Serbin
Keyword(s):  
Mathematical Models ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Three Dimensional ◽  
Fuel Mixture ◽  
Gas Turbine Engine ◽  
Operational Parameters ◽  
Combustion Chambers ◽  
Turbine Engine ◽  
Low Emission

The appliance of modern tools of the computational fluid dynamics for the investigation of the pulsation processes in the combustion chamber caused by the design features of flame tubes and aerodynamic interaction compressor, combustor and turbine is discussed. The aim of the research is to investigate and forecast the non-stationary processes in the gas turbine combustion chambers. The results of the numerical experiments which were carried out using three-dimensional mathematical models in gaseous fuels combustion chambers reflect sufficiently the physical and chemical processes of the unsteady combustion and can be recommended to optimize the geometrical and operational parameters of the low-emission combustion chamber. The appliance of such mathematical models are reasonable for the development of new samples of combustors which operate at the lean air-fuel mixture as well as for the modernization of the existing chambers with the aim to develop the constructive measures aimed at reducing the probability of the occurrence of the pulsation combustion modes. Keywords: gas turbine engine, combustor, turbulent combustion, pulsation combustion, numerical methods, mathematical simulation.

scholarly journals Improving Survivability of Aircraft from Uncontained Gas Turbine Engine Failures

2011 ◽  
Vol 133 (08) ◽  
pp. 56-57
Author(s):  
Chris Adams ◽  
John Manion
Keyword(s):  
Gas Turbine ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Assessment Model ◽  
Hazard Evaluation ◽  
Commercial Aircraft ◽  
Turbine Engine ◽  
Geometry Model ◽  
Us Military ◽  
Aircraft Component

This article describes new measures to improve survivability of aircraft from uncontained gas turbine engine failures. The US military has adopted a common tool—Uncontained Engine Debris Damage Assessment Model (UEDDAM)—for its methodology to consider uncontained events in a more realistic manner. UEDDAM can handle the analysis for the release of the primary rotor-disk segment plus smaller engine debris fragments in directions out of the plane of rotation. The UEDDAM code requires an input of a three-dimensional geometric description of aircraft component positions within the aircraft and thus, in relationship to each other. The description uses a specific input format. Adopting an assessment methodology, like UEDDAM, results in a universal standard and uniformity of debris hazard evaluation across the involved agencies. Maintaining the 3D aircraft geometry model and its components/system functional flow data generated by aircraft manufacturers during their initial hazard assessment would simplify later debris hazard reassessments required by maintenance, repair, or military-modification to a commercial aircraft.

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