An integrated gas supply device
A gas supply and integrated technology, which is applied in the direction of jet propulsion devices, rocket engine devices, machines/engines, etc., can solve the problems of large cross-sectional size envelope, low engine integration, and affecting engine performance, so as to achieve consistent filling time, The effect of compact structure and light weight
Active Publication Date: 2020-11-06
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0004] In order to solve the technical problems that the existing air turbine rocket engine has an external gas supply, which makes the engine integration low, the envelope of the cross-sectional size is large, and affects the performance of the engine, the present invention provides an integrated gas supply device
Method used
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[0041] The content of the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0042] Such as figure 1 with figure 2 As shown, an integrated gas supply device includes a fuel supply unit, an oxidant supply unit, a protection unit, a vane part 2, a pressure measurement unit, a cooling and lubrication unit, and a shafting sleeve 5 coaxially arranged sequentially from the inside to the outside. , Combustion organization part 1, shell;
[0043] The housing includes an inner ring housing 4, an outer ring housing 3 coaxially arranged with the inner ring housing 4, and 10 hollow support plates 8, 10 arranged between the inner ring housing 4 and the outer ring housing 3 A hollow support plate 8 is evenly distributed along the circumferential direction, and the annular passage between the inner ring housing 4 and the outer ring housing 3 is divided into 10 equally spaced small passages; two hollow suppo...
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The invention provides an integrated gas supply device. The problems that a gas supply device of an existing air turbine rocket engine makes an engine low in integration degree, a sectional dimensionenvelope is large, and the performance of the engine is affected are solved. The device includes a fuel supply unit, an oxidizing agent supply unit, a protection unit and a stationary blade part, andfurther includes a shafting sleeve, a combustion structure part and a shell which are successively and coaxially arranged from inside to outside, the shell includes an inner ring shell, an outer ringshell and N hollow support plates arranged between the inner ring shell and the outer ring shell, the N hollow support plates are evenly distributed in the peripheral direction, the combustion structure part includes an annular injector and an annular body part, the protection unit includes an inner ring thermal protection piece and an outer ring thermal protection piece, the fuel supply unit includes a fuel valve arranged on the outer wall of the outer ring shell and two fuel supply assemblies symmetrically arranged on both sides of the fuel valve, and the oxidizing agent supply unit includesan oxidizing agent valve arranged on the outer wall of the outer ring shell and two oxidizing agent supply assemblies symmetrically arranged on both sides of the oxidizing agent valve.
Description
technical field [0001] The invention belongs to the technology of an air-breathing combined power engine, and in particular relates to an integrated gas supply device, which is applicable to an air turbine rocket engine. Background technique [0002] The air-breathing combined power is the research direction of the main power of the future space-to-earth reusable aircraft. The air-turbine rocket engine is a relatively mature air-breathing combined power engine. After being mixed with the fuel-rich gas in the mixer, it enters the combustion chamber to burn to generate thrust. [0003] The gas supply of existing air turbine rocket engines is provided by independent combustion components placed outside the engine cylinder. The gas radially passes through the air flow channel and enters the internal gas collection chamber to drive the turbine, which makes the engine integration level low, and the cross-sectional size includes If the network is large, it will have a great impact...
Claims
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IPC IPC(8): F02K9/44F02K9/52F02K9/60F02K9/62F02K9/42F01D9/04
CPCF01D9/041F02K9/42F02K9/44F02K9/52F02K9/60F02K9/62
Inventor 李哲南向谊马元逯婉若李光熙朱东华刘新华朱岩
Owner XIAN AEROSPACE PROPULSION INST