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Active cooling and combustion decoupling system of scramjet engine

A scramjet and active cooling technology, which is applied to the cooling of engines, ramjet engines, engine components, etc., can solve the problems of reducing cooling fuel flow and unsuitable supercritical carbon dioxide system layout, etc., to reduce cooling fuel flow, The effect of reducing heat and ensuring safe and reliable work

Inactive Publication Date: 2021-02-19
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

But when used as a cooling system, the main goal is to reduce the cooling fuel flow rather than pursue high thermal efficiency, so the traditional supercritical carbon dioxide system layout is not suitable, and it needs to be improved to apply to scramjet engines to obtain optimal cooling Effect

Method used

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  • Active cooling and combustion decoupling system of scramjet engine

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Embodiment 1

[0028] refer to figure 1 The scramjet active cooling and combustion decoupling system provided in this embodiment includes a scramjet 1, a first wall cooling channel 2, a second wall cooling channel 3, a fuel tank 4, a fuel pump 5, and a turbine 6 , generator 7, high temperature regenerator 8, low temperature regenerator 9, second compressor 10, first compressor 11, fuel heat exchanger 12 and diverter valve 13.

[0029] In order to ensure that the fuel has a sufficiently high temperature rise and reduce the flow rate of the cooling fuel to the greatest extent, this embodiment proposes two measures: one is to change the split flow position of the traditional recompression supercritical carbon dioxide cycle, and to split the flow at the outlet of the turbine to This increases the inlet temperature of the thermal fluid in the fuel heat exchanger. The second is to increase the temperature of carbon dioxide at the inlet of the compressor so that it is higher than the critical temp...

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Abstract

The invention provides an active cooling and combustion decoupling system of a scramjet engine. According to the active cooling and combustion decoupling system of the scramjet engine, a first wall face cooling channel is arranged on an air inlet channel and an isolation section of the scramjet engine, and a second wall face cooling channel is arranged on a combustion chamber and an exhaust nozzleof the scramjet engine. In the combustion chamber and exhaust nozzle area with high thermal loads, supercritical carbon dioxide is used for absorbing heat and raising the temperature through the second wall face cooling channel. Hydrocarbon fuel is adopted for cooling in he air inlet channel and the isolation section with low thermal loads. According to the system, active cooling and combustion decoupling of the scramjet engine can be achieved, meanwhile, the flow of fuel needed for cooling can be reduced, and the cooling pressure of the scramjet engine is relieved.

Description

technical field [0001] The invention relates to the technical field of scramjet active thermal protection, in particular to a scramjet active cooling and combustion decoupling system based on a supercritical carbon dioxide cycle. Background technique [0002] The scramjet engine is an ideal power plant for a hypersonic vehicle (usually an aircraft with a flying Mach number greater than 5). It does not need to carry an oxidant, has a higher specific impulse than a rocket engine, and has higher working efficiency at a high Mach number . As hypersonic vehicles receive more and more attention, scramjet and its related technologies have also become a hot topic of research at home and abroad in recent years. [0003] Due to the long-time, high Mach number flight, high enthalpy flow and combustion heat release, the scramjet faces a harsh thermal environment. For example, when the flight Mach number reaches 6, the gas temperature in the combustion chamber can reach as high as 2800...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/14F02C7/18F02C7/16F02C7/224F01K27/02F01K25/10F01K7/32F01D15/10
CPCF01D15/10F01K7/32F01K25/103F01K27/02F02C7/16F02C7/185F02C7/224F02K7/14
Inventor 苗鹤洋王中伟钮耀斌杨烜
Owner NAT UNIV OF DEFENSE TECH
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