Heat returning closed cooling recirculation system of Brighton scramjet

A technology of engine cooling and scramjet, which is applied to ramjet engines, machines/engines, rocket engine devices, etc., and can solve the problems of scramjet cooling difficulties, fuel supply system gas intake difficulties, and large cooling fuel flow, etc. problems, to achieve the effect of improving energy utilization, good component matching performance, and good heat absorption performance

Inactive Publication Date: 2009-11-11
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problems of the existing hypersonic vehicle scramjet cooling difficulties, large cooling fuel flow,

Method used

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  • Heat returning closed cooling recirculation system of Brighton scramjet
  • Heat returning closed cooling recirculation system of Brighton scramjet

Examples

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Example Embodiment

[0009] Specific implementation mode 1: Combination figure 1 To illustrate this embodiment, the cooling cycle system includes a compressor 1, an engine 3, a cooling channel 4, a turbine 5, a fuel tank 7, a fuel pump 8, and a central shaft 10. The cooling cycle system also includes a heat regenerator 2, Heater 6 and generator 9, one end of the central shaft 10 is connected to the generator 9, the other end of the central shaft 10 is respectively connected to the compressor 1 and the fuel pump 8, the turbine 5 is installed in the generator 9 and On the central shaft 10 between the compressor 1, the cooling channel 4 is arranged on the outer wall surface of the upper part of the engine 3; the output end of the compressor 1 is connected to the cold side input end of the regenerator 2 through a pipeline, The cold side output end of the regenerator 2 is connected to the input end of the cooling channel 4 through a pipeline, the output end of the cooling channel 4 is connected to the inp...

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Abstract

The invention discloses a heating returning closed cooling recirculation system of a Brighton scramjet, which relates to a cooling recirculation system of a scramjet. The invention aims at solving the problems of cooling difficulty, a large amount of cooling fuel flow, insufficient heat sink and gas-fetching difficulty of the fuel supply system of the scramjet of a prior hypersonic aerial vehicle. One end of a central axis is connected with a generator and another end thereof is respectively connected with a gas compressor and a fuel pump. A turbine is arranged on the central axis between the generator and the gas compressor. A cooling channel is arranged on the external wall at the upper part of the scramjet. The cooling recirculation system is provided with a primary cooling loop and a secondary cooling loop. The cooling recirculation system of the scramjet is applicable to the thermal protection of the hypersonic aerial vehicle and the cooling of the scramjet.

Description

technical field [0001] The invention relates to a cooling cycle system of a scramjet engine. Background technique [0002] Hypersonic vehicles with a flying Mach number greater than 5 are a hot topic in current research, including the development of single-stage or two-stage orbital space planes, space-to-ground transport vehicles, and hypersonic cruise missiles. One of the key technologies of the air-breathing hypersonic vehicle with the scramjet engine as the propulsion system is the thermal protection of the vehicle, in which the cooling of the engine is the most difficult part, because even if composite materials are used, it is difficult to withstand the huge heat generated inside the engine. heat load. It is generally believed that fuel is the best coolant, but theoretical analysis and practice show that the coolant flow rate will be greater than the propulsion fuel flow rate after reaching a certain flight Mach number, so extra fuel has to be carried, and the excess ...

Claims

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Application Information

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IPC IPC(8): F02K7/10F02K9/64
Inventor 鲍文秦江于达仁周伟星
Owner HARBIN INST OF TECH
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