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Combined cycle engine and hypersonic aircraft

A technology of engine and ramjet, which is applied to the cooling of engine components, machines/engines, and engines. It can solve the problems of difficult mode conversion, long combustion chamber length, and low thermal cycle efficiency, and achieve low conversion difficulty and high thrust. The effect of excellent performance and excellent economic performance

Active Publication Date: 2018-11-06
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The invention provides a combined cycle engine and a hypersonic aircraft to solve the technical problems of traditional RBCC engines with many working modes, difficult mode conversion, low thermal cycle efficiency, poor thrust performance and long combustion chamber length

Method used

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  • Combined cycle engine and hypersonic aircraft

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Embodiment Construction

[0030]The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in many different ways defined and covered by the claims.

[0031] refer to Figure 4 , the preferred embodiment of the present invention provides a combined cycle engine, comprising a rotary detonation ramjet engine 10 and a rocket engine 20 disposed therein. The rotary detonation ramjet engine 10 includes: a casing 11 , the casing 11 is in the shape of a hollow cylinder whose two ends are connected. Also includes a central cone 12, the rear body 121 of the central cone 12 extends into the housing 11 from the intake end of the housing 11 and is connected to the housing 11, and the gap between the housing 11 and the rear body 121 forms the introduction of air into the housing 11 The drainage channel 101 inside, the cavity between the rear end surface of the rear body 121 and the inner wall of the shell 11 fo...

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Abstract

The invention discloses a combined cycle engine and a hypersonic aircraft which includes a rotary detonation ramjet engine and a rocket engine arranged therein. The rotary detonation ramjet engine includes a shell and a conical inner body, wherein the shell is in a hollow cylindrical shape and two ends communicate, and the after body of the conical inner body stretches into the shell from an air inlet end of the shell and is connected with the shell. And a gap between the shell and the after body forms a drainage channel for air to be led in the shell. A cavity between the rear end surface ofthe after body and the inner wall of the shell forms a detonation chamber which communicates with the drainage channel, and a first exhaust nozzle communicates with the detonation chamber. The rocketengine includes a combustion chamber arranged in the conical inner body, a second exhaust nozzle communicating with the combustion chamber, and the nozzle of the second exhaust nozzle communicates with the detonation chamber. The outer wall of the shell is machined with an outer nozzle, the two ends of the outer nozzle correspondingly communicates with a fuel supply device and the drainage channel. The outer wall of and / or the after body is machined with multiple internal nozzles, two ends of the internal nozzles correspondingly communicate with the fuel supply device and the drainage channel.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to a combined cycle engine. In addition, the present invention also relates to a hypersonic aircraft comprising the above-mentioned combined cycle engine. Background technique [0002] The hypersonic vehicle flies faster than 5 times the speed of sound and usually flies at an altitude of 18-35 kilometers. It is a new type of "killer" weapon with long-range, fast and precise strike capabilities. Supersonic propulsion technology. A scramjet is a hypersonic propulsion device that has been extensively studied, and it organizes combustion in an isobaric mode. Continuous rotary detonation ramjet is a new type of ramjet propulsion scheme proposed recently. It organizes combustion in detonation mode, which has higher thermal cycle efficiency than isobaric combustion, and is expected to provide a higher-performance power plant for hypersonic vehicles. Literature [Wang Chao, Liu Weidong, Liu Shi...

Claims

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Application Information

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IPC IPC(8): F02C3/14F02C3/32F02C7/00F02C7/12F02K1/78
CPCF02C3/14F02C3/32F02C7/00F02C7/12F02K1/78
Inventor 刘世杰刘卫东张海龙林志勇孙明波王翼蒋露欣任春雷
Owner NAT UNIV OF DEFENSE TECH
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