Open AccessDETERMINATION OF HYDRAULIC LOSSES BASED ON FLOW SIMULATION IN THE ELEMENTS OF THE COMBUSTION CHAMBER OF A GAS TURBINE ENGINE
Author(s) -
Yu. K. Aleksandrov,
Nguyen The Dat,
Б. Г. Мингазов
Publication year - 2021
Publication title -
vestnik permskogo nacionalʹnogo issledovatelʹskogo politehničeskogo universiteta. aèrokosmičeskaâ tehnika
Language(s) - English
Resource type - Journals
eISSN - 2304-6457
pISSN - 2224-9982
DOI - 10.15593/2224-9982/2021.65.01
Subject(s) - combustion chamber , mechanics , combustion , turbulence , flow (mathematics) , mechanical engineering , materials science , thermodynamics , engineering , chemistry , physics , organic chemistry
The article presents the results of the study of hydraulic characteristics using the example of the combustion chamber of the aircraft engine PS-90A. A mathematical model of gas dynamics of the combustion chamber based on the equations of one-dimensional stationary flow is considered. In a one-dimensional formulation, the change in parameters along the path of the combustion chamber is analyzed for various modes of engine operation, from idle to takeoff. The boundary conditions for each model were obtained based on the results of thermogasdynamic calculations. All modes of operation of the combustion cham-ber were considered with combustion and without combustion of liquid fuel. The numerical three-dimensional model provided for the calculation of one sector of the combustion chamber containing one flame tube of a tubular-annular type with a concentrical-ly installed two-row swirler. The grid model was selected based on the calculation results from several options according to the condition of grid independence of the selected parameters. The calculation took into account the effects of turbulence, chemical interaction of fuel with air supplied from the engine compressor. For the reliability of the temperature distribution in the area of the flame tube, a calculation was made taking into account the model of radiant heat transfer. The calculation of the combustion of a premixed mixture was carried out in a non-adiabatic formulation using the model of a thin flame front and in the gas-phase approximation. The main features of the flow and changes in pressures and flow rates in the flow path of the combustion cham-ber are described. It has been established that the main losses occur in the diffuser and the frontal arrangement of the combus-tion chamber. A comparison of the results obtained in a one-dimensional formulation with numerical calculations in a three-dimensional formulation was made, which showed their correspondence with each other with the permissible level of deviation.