Hypersonic flight vehicle engine heat recovery power generation system and control method thereof

Abstract

The invention provides a hypersonic flight vehicle engine heat recovery power generation system and a control method thereof. CO2 is heated in a hypersonic flight vehicle engine wall face heat absorption channel to enter a supercritical CO2 turbine to swell to act, output CO2 exhaust air releases heat through low-pressure side channels of multiple heat regenerators and absorbs heat through high-pressure side channels, air exhaust compression is carried out in the process that CO2 exhaust air fluid enters multiple compressors and the corresponding heat regenerators from multiple fuel coolers, the heat capacities of different-pressure CO2 exhaust air fluid in the high-pressure side channel and the low-pressure side channel of each heat regenerator are close, and the heat capacity of the CO2 exhaust air fluid in a heat fluid channel and a cold fluid channel of each fuel cooler and the heat capacity of fuel fluid for cooling are close. By means of the hypersonic flight vehicle engine heat recovery power generation system and the control method, the heat of the engine wall face can be efficiently converted into electric energy and compressor power; and meanwhile, the heat recovery rate is improved, the amount of fuel for cooling is reduced, and cost is saved.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft engines, in particular to a hypersonic aircraft engine heat recovery power generation system and a control method thereof. Background technique [0002] During the flight of a hypersonic vehicle, hot components are subjected to high heat flux density, and thermal protection technology has become one of the key technologies for success or failure. Among them, the thermal protection of hypersonic aircraft engines is the most important thing. The heat flux density of the engine combustion chamber wall is high, the gas temperature is high, the thermal protection area is large, and the required amount of coolant is large. It is necessary to adopt a compact and efficient method for thermal protection of the engine. [0003] The conventional thermal protection method of hypersonic aircraft engine is to use fuel to convectively cool the engine wall, and the fuel absorbs heat and enters the eng...

AI Technical Summary

Problems solved by technology

However, there is currently no relevant solution to solve the heat capacity flow matching problem of the fluid in the hot fluid channel and the cold fluid channel in the regenerator and fuel cooler

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