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Closed cycle heat management integrated system based on supercritical medium

A closed-loop, integrated system technology, used in engine cooling, ramjet engine, turbine/propulsion cooling, etc., can solve the problem of difficult design of high-power air turbine pumps, large impact on aircraft performance and weight, and fuel coking. Cooling failure and other problems, to avoid the risk of gasification coking, solve the problem of insufficient fuel heat sink, and reduce the temperature rise of fuel

Inactive Publication Date: 2021-01-01
AECC SICHUAN GAS TURBINE RES INST
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Problems solved by technology

2) Fuel regenerative cooling has the risk of fuel coking and cooling failure. At present, dual-mode ramjet engines or scramjet engines use fuel to cool hot walls such as the engine's intake port, combustion chamber, and nozzle.
The traditional comprehensive energy solution based on ram air turbine for power extraction has a narrow working Mach number range, high-power air turbo pump design is difficult, and has a great impact on aircraft performance and weight.

Method used

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  • Closed cycle heat management integrated system based on supercritical medium

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Embodiment Construction

[0025] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0026] It should be understood that the terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" may also be meant to include the plural forms unless the context clearly dictates otherwise. The terms "comprising", "comprising", "containing" and "having" are inclusive and thus indicate the presence of stated...

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Abstract

The invention provides a closed cycle heat management integrated system based on a supercritical medium. The system comprises an engine cooling subsystem, a cooling medium compression subsystem, a power output subsystem, a regenerative subsystem and a fuel oil heat exchange subsystem. According to the closed cycle heat management integrated system based on the supercritical medium, supercritical carbon dioxide serves as the medium, and a micro-channel efficient heat exchanger is adopted so that power can be output while the wall temperature of a hot end is reduced. Compared with a fuel oil direct cooling scheme, the fuel oil temperature rise can be reduced, the gasification coking risk of fuel oil is avoided, and the problems of insufficient fuel oil heat sink and the like are solved. Thesupercritical carbon dioxide subjected to heat absorption can utilize turbine expansion to output power or generate electricity. About 30%-40% of heat (the current domestic closed cycle efficiency isabout 30%) can be converted into shaft work or electricity to be utilized, and the problem about power extraction of a comprehensive energy system can be solved.

Description

technical field [0001] The invention belongs to the field of turbo-ramjet combined engines, and in particular relates to a closed-cycle heat management integrated system based on supercritical medium. Background technique [0002] The turbo-ramjet combined engine (TBCC) used in high Mach number aircraft has the characteristics of wide flight envelope, high flight speed, zero-speed take-off, and reusability, and is a very promising combination power. However, due to factors such as poor cooling air quality, high combustion temperature, and large cooling area at high Mach numbers, it is extremely difficult to design a comprehensive thermal management system for a TBCC engine. At the same time, the energy demand in the full envelope of the aircraft and its combined engine is large (reaching the megawatt level), and the design of the integrated energy system is difficult. [0003] The specific problems have the following three aspects: 1) the cooling problem of the large-area c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/18F02K7/16F02K1/82F01K23/02F01K25/10
CPCF01K23/02F01K25/103F02C7/18F02K1/822F02K7/16
Inventor 娄德仓李丹赵维维王伟田山林周雷袁彪
Owner AECC SICHUAN GAS TURBINE RES INST
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