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

A hypersonic, heat recovery technology, applied in machine/engine, engine functions, engine components, etc., can solve problems such as heat capacity flow matching, achieve optimal heat transfer temperature difference, improve heat recovery utilization, and reduce irreversible losses. Effect

Active Publication Date: 2017-05-10
TSINGHUA UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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

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Embodiment Construction

[0031] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary only for explaining the present invention and should not be construed as limiting the present invention.

[0032] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner" and "outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and Simplified descriptions, rather than indicating or implying that the device or element refe...

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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01K25/10F01K7/32F01K17/06F01K13/02F02C7/18F02C7/16
CPCF01K7/32F01K13/02F01K17/06F01K25/103F02C7/16F02C7/18F05D2220/80F05D2260/20
Inventor 姜培学胥蕊娜祝银海张富珍欧阳小龙王超
Owner TSINGHUA UNIV
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