Inlet total temperature synthesis for gas turbine engines

Details Inlet total temperature synthesis for gas turbine engines Inlet total temperature synthesis for gas turbine engines

F - Mech Eng,Light,Heat,Weapons

02

C

354/29

F02C 9/28 (2006.01)

Patent

CA 1286774

Abstract Inlet Total Temperature Synthesis for Gas Turbine Engines In a gas turbine engine electronic control system the engine total inlet temperature is synthesized from aircraft Mach number and the nozzle expansion ratio. When the engine is in a transient mode of operation the synthesized value of the total inlet temperature is maintained constant at the value calculated just before entering the transient mode. The synthesized temperature is used when the actual measured temperature is unavailable or unreliable.

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