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Shell structure of air-breathing stamping rotary knocking engine adopting liquid state fuel

A detonation engine and liquid fuel technology, applied in ramjet engines, engine components, machines/engines, etc., can solve the problems of rapid atomization and difficult evaporation, shorten preparation time, shorten axial length, enhance effect of effect

Active Publication Date: 2020-09-15
XIAN AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

Method used

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  • Shell structure of air-breathing stamping rotary knocking engine adopting liquid state fuel

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Embodiment

[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 central 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 c...

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Abstract

The invention relates to an air-breathing engine adopting a liquid state fuel, in particular to a shell structure of an air-breathing stamping rotary knocking engine adopting a liquid state fuel. Theinvention aims to solve the technical problem of quick atomization and relatively large evaporation difficulty in the prior art and provides the shell structure of the air-breathing stamping rotary knocking engine adopting the liquid state fuel. The structure comprises an engine outer shell and a premixed gas shell assembly which comprises an air inlet cone, an isolation section center body and acombustion chamber center body. The isolation section center body is connected to the engine outer shell through a main supporting rod; the air inlet cone is connected to the isolation section centerbody through a front supporting rod, and a circular seam-shaped air inlet channel is formed between the air inlet cone and the isolation section center body; the combustion chamber center body is connected to the isolation section center body through a back supporting rod, and a circular seam-shaped injection channel is formed between the combustion chamber center body and the isolation section center body; a fuel box and a nozzle are arranged in the air inlet cone; and a mixing chamber is arranged in the isolation section center body and the mixing chamber communicates to 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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Application Information

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IPC IPC(8): F01D25/26F02C7/22F02C7/04F02K7/10
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
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