Analysis of turbojet combustion chamber performances based on flow field simplified mathematical model

In this paper are presented some results about the study of combustion chamber geometrical configurations that are found in aircraft gas turbine engines. The main focus of this paper consists in a study of a new configuration of the aircraft engine combustion chamber with an optimal distribution of...

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Bibliographic Details
Main Author: Rotaru, Constantin
Format: Conference Proceeding
Language:English
Subjects:
Air cooling
Aircraft
Aircraft engines
Combustion chambers
Computer simulation
Configurations
Dilution
Fuel injection
Gas turbine engines
Injectors
Nonuniformity
Pressure ratio
Secondary flow
Turbojet engines
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Summary:In this paper are presented some results about the study of combustion chamber geometrical configurations that are found in aircraft gas turbine engines. The main focus of this paper consists in a study of a new configuration of the aircraft engine combustion chamber with an optimal distribution of gas velocity in front of the turbine. This constructive solution could allow a lower engine rotational speed, a lower temperature in front of the first stage of the turbine and the possibility to increase the turbine pressure ratio. The Arrhenius relationship, which describes the basic dependencies of the reaction rate on pressure, temperature and concentration has been used. and the CFD simulations were made with jet A fuel (which is presented in the Fluent software database) for an annular flame tube with 24 injectors. The temperature profile at the turbine inlet exhibits nonuniformity due to the number of fuel injectors used in the circumferential direction, the spatial nonuniformity in dilution air cooling and mixing characteristics as well as other secondary flow patterns and instabilities that are set up in the flame tube.
ISSN:0094-243X
1551-7616
DOI:10.1063/1.4981987