An Investigation of Gas Turbine Combustors with High Inlet Air Temperatures. Part 2; Heat Transfer
Annual rept. no. 2, Mar 1970-Mar 1971
PURDUE UNIV LAFAYETTE IN JET PROPULSION CENTER
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The wall temperature distribution of a combustion chamber is a function of the various heat transfer processes existing in the chamber and annulus. The basic turbulent conservation equations of mass, momentum, species, and energy are developed in an effort to provide an analytical rather than empirical method of determining the temperature distribution. However, the inclusion of radiation energy exchange using the radiative transport theory and the fact that the chamber flow is not one dimensional makes a closed form solution to the problem mathematically impossible.
- Combat Vehicles
- Combustion and Ignition
- Jet and Gas Turbine Engines