High-Mach-number aero-engine compartment and turbine disc combined cooling thermal management system

Abstract

The invention provides a high-Mach-number aero-engine compartment and turbine disc combined cooling thermal management system which comprises an engine air main flow path, and the engine air main flow path comprises a cold air inlet channel, an air compressor, a main combustion chamber, a turbine and an afterburner which are sequentially communicated in the air flowing direction. The system further comprises an air-air heat exchanger and an air-oil heat exchanger, the cold air inlet end of the air-air heat exchanger is communicated with the cold air inlet channel, the hot air inlet end of the air-air heat exchanger is communicated with the hot air exhaust end of the air compressor, the hot air exhaust end of the air-air heat exchanger is communicated with the hot air inlet end of the air-oil heat exchanger, and the air-oil heat exchanger further comprises a cold fuel oil input end. The air output end of the air-oil heat exchanger is connected with the cooling air inlet end of the turbine. The thermal management system can simultaneously solve the problems that in a high-speed aircraft, the temperature in an aero-engine compartment is high, accessories cannot work normally, the air entraining temperature of an air compressor is high, and a turbine disc overheats.

Description

technical field [0001] The present disclosure relates to the technical field of thermal management of aero-engines, in particular to a thermal management system for combined cooling of a high Mach number aero-engine compartment and a turbine disk. Background technique [0002] As the flight speed of aircraft becomes higher and higher, the problem of heat becomes more and more prominent in the design of aero-engines. The thermal management system plays an increasingly important role in aero-engines, and it is an important factor to ensure that the various systems of the engine can work normally. However, the traditional relatively simple thermal management scheme has been unable to meet the current working requirements under high-speed flight conditions. The cooling bleed air of the turbine disk adopts the outlet air of the compressor. Since the temperature of the compressor outlet is getting higher and higher, if the air entering the turbine disk is not cooled, the temperat...

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Problems solved by technology

[0005] In view of this, the embodiment of the present disclosure provides a high Mach number aero engine compartment and a combined cooling thermal management system of the turbine disk. The thermal management system of the present invention can simultaneously solve the problem of high temperature in the aero-engine compartment of high-speed aircraft and failure of accessories to work normally. and the problem of high compressor bleed air temperature and turbine disk overheating

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