Combined type scramjet engine cooling circulation system

A technology of engine cooling and scramjet, which is applied in the direction of engine cooling, engine components, turbine/propulsion device cooling, etc., can solve the problems of scramjet regenerative cooling difficulties, excessive cracking and coking of cooling fuel, etc., to avoid transmission Heat worsens extreme working conditions, weakens the wall temperature, and avoids the effect of blocking the cooling channel

Active Publication Date: 2021-03-02
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0006] In order to avoid the deficiencies of the prior art, the present invention proposes a combined scramjet cooling cycle system, which combines open and closed cycles, and uses liquid metal for heat exchange in the closed cycle, which solves the problem of overheating For the problems of difficult...

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  • Combined type scramjet engine cooling circulation system
  • Combined type scramjet engine cooling circulation system

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Embodiment Construction

[0019] The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0020] refer to figure 1 Said, a combined scramjet cooling cycle system of the present invention comprises an open cooling cycle system and a closed cooling cycle system; the working fluid in the open cooling cycle system is kerosene; the closed cooling cycle The working medium in the system is liquid metal, and the liquid metal is one or more combinations of lead, sodium, lithium, cesium, rubidium, sodium-potassium alloy, lead-bismuth alloy, lithium-lead alloy and doped indium alloy.

[0021] The open cooling circulation system is actually the fuel flow cooling side, including fuel tank 1, fuel pump 2, heat exchanger 3, first cooling passage 4, fuel injector 5, and all components are connected by pipelines . The fuel tank 1 is connected to the inlet of the fuel pump 2, the heat exc...

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Abstract

The invention discloses a combined type scramjet engine cooling circulation system, and belongs to the technical field of air suction type scramjet engine thermal protection. The system comprises a fuel tank, a fuel pump, a heat exchanger, a first cooling channel, a second cooling channel, a fuel injector and an electromagnetic pump; an annular cavity is formed between the inner wall face and theouter wall face of an engine outer shell and divided into the first cooling channel and the second cooling channel; the fuel tank, the fuel pump, the heat exchanger, the first cooling channel and thefuel injector are sequentially connected through pipelines to form an open cooling circulation system, and kerosene serves as a working medium; and the electromagnetic pump, the second cooling channeland the heat exchanger are sequentially connected through pipelines to form a closed cooling circulation system, and the working medium is liquid metal. According to the combined type scramjet enginecooling circulation system, waste heat of the wall face of an engine combustion chamber is utilized, the advantages of an active regeneration cooling system are reserved, the problems of heat transfer deterioration, cracking coking and the like of a traditional cooling working medium are solved, and an efficient energy management circulating system is constructed.

Description

technical field [0001] The invention belongs to the technical field of thermal protection of an air-breathing scramjet, and in particular relates to a combined cooling cycle system of a scramjet. Background technique [0002] The development of advanced hypersonic aircraft is an important symbol of a country's comprehensive strength, and it has great significance for military strategy, national economy, and social life. The current aircraft with Mach number Ma>5 is the product of human pursuit of higher flight speeds. However, with the increase in the demand for flight Mach number and cruise time, due to the high enthalpy flow and combustion heat release, the thermal environment of the combustion chamber is extremely harsh, and the problem of cooling the engine wall of advanced aircraft is becoming more and more prominent. For example, when the flight altitude of the scramjet engine is 25km and the Mach number reaches 6.5, the aircraft will withstand the inlet air tempera...

Claims

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Application Information

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IPC IPC(8): F02C7/22F02C7/224F02C7/16F23R3/00F23R3/28
CPCF02C7/22F02C7/224F02C7/16F23R3/002F23R3/005F23R3/283
Inventor 谢公南孙丰李勇
Owner NORTHWESTERN POLYTECHNICAL UNIV
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