Shell structure of liquid fuel air-breathing ram rotary detonation engine
A detonation engine, liquid fuel technology, applied in ramjet engines, engine components, machines/engines, etc., can solve the problems of rapid atomization and difficult evaporation, shorten the preparation time, reduce the difficulty of detonation, and shorten the axis effect on length
Active Publication Date: 2022-04-12
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
[0008] The purpose of the present invention is to solve the technical problems of rapid atomization and evaporation in the prior art, and to provide a liquid fuel air-breathing ram rotary detonation engine shell structure
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[0045] A shell structure of a liquid fuel air-breathing ram rotary detonation engine, comprising an intake cone 21 , a central body 22 of an isolation section, a central body 23 of a combustion chamber and an outer casing 1 of the engine. The intake cone 21 is connected to the center body 22 of the isolation section through four front support rods 25 arranged in the circumferential direction, and the center body 22 of the isolation section is connected to the center body 23 of the combustion chamber through four rear support rods 27 arranged in the circumferential direction. The outer shell 1 and the center body 22 of the isolation section are connected by four main support rods 24 arranged in the circumferential direction. Fuel tank and fuel injector are arranged in the air intake cone 21, and the annular slot-shaped air intake channel 26 is arranged between the air intake cone 21 and the center body 22 of the isolation section, and the mixing chamber 221 is arranged in the ce...
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The invention relates to an air-breathing engine using liquid fuel, in particular to a shell structure of an air-breathing ram rotary detonation engine using liquid fuel. The purpose of the present invention is to solve the technical problems of rapid atomization and evaporation in the prior art, and to provide a liquid fuel air-breathing ram rotary detonation engine shell structure. The structure includes the engine outer casing and the premixed gas casing assembly including the intake cone, the isolation section center body and the combustion chamber center body; the isolation section center body is connected to the engine outer casing through the main support rod; the intake cone is connected through the front support rod The central body of the isolation section forms an annular seam-shaped air intake channel between the air intake cone and the central body of the isolation section; the central body of the combustion chamber connects the central body of the isolation section through the rear support rod, and is between the central body of the combustion chamber and the central body of the isolation section An annular slot-shaped injection channel is formed; a fuel tank and a nozzle are arranged in the intake cone; a mixing chamber is opened in the center body of the isolation section, and the mixing chamber communicates with the nozzle.
Description
technical field [0001] The present invention relates to an air-breathing engine using liquid fuel, in particular to a shell structure of an air-breathing ram rotary detonation engine using liquid fuel. The engine adopting this shell structure can operate within a wide range of Mach numbers. Reliable work, can be used as the power of drones, and can also be used in other equipment that requires high performance, low-cost air-breathing power. Background technique [0002] Rotating detonation combustion is different from the isobaric combustion widely used in current engines. It is essentially a supersonic combustion process that achieves an extremely fast chemical reaction with a low entropy increase. It has a fast energy release rate (approximate isovolumic combustion ), high thermal cycle efficiency, etc. In addition, due to the self-supercharging nature of the detonation wave, a certain combustion supercharging ratio can be achieved, and the power system based on detonatio...
Claims
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IPC IPC(8): F02K7/10F01D25/26F02C7/22F02C7/04
CPCF01D25/26F02C7/22F02C7/04F02K7/10
Inventor 严宇王永佳杨宝娥胡洪波陈宏玉冯建畅尚帅
Owner XIAN AEROSPACE PROPULSION INST