Air-breathing rotary detonation wave injection and multimode ram detonation coupled circulating propulsion system

A detonation wave and multi-mode technology, applied in jet propulsion devices, ramjet engines, machines/engines, etc., can solve the problem of difficult adjustment and reserve of net thrust, large engine external resistance, and limitation of aircraft flight speed And other issues

Inactive Publication Date: 2012-07-18
董国光
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Problems solved by technology

For aircraft operating at hypersonic speeds, the entropy increase of shock wave compression and supersonic combustion is very serious, which makes the available power of the system drop rapidly. The flight speed of the aircraft

Method used

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  • Air-breathing rotary detonation wave injection and multimode ram detonation coupled circulating propulsion system
  • Air-breathing rotary detonation wave injection and multimode ram detonation coupled circulating propulsion system
  • Air-breathing rotary detonation wave injection and multimode ram detonation coupled circulating propulsion system

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Embodiment Construction

[0025] In order to make the propulsion system have high specific impulse, high thrust coefficient, and high thrust-to-weight ratio under wide flight conditions, it is necessary to inject fuel into the supernatural ramjet multiple times and accelerate the flow velocity of the flow field. In the flow field of the propulsion system, the premixed gas can be inhaled multiple times through the lobe ejection nozzle. The ejection inlet is set above the aircraft, which can increase the lift of the aircraft. The annular phase detonation can still be set in the expansion tail nozzle wave control system.

[0026]From the thermodynamic cycle process of the air-breathing rotating detonation wave ejection multi-mode ram-detonation coupling propulsion system, it can be known that the rotating detonation wave gas jet acts as the igniter of the ramjet engine, and from the ejection of the incoming air to the hypersonic speed flow can form a stable combustion. This forced detonation method allow...

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Abstract

The invention provides an air-breathing rotary detonation wave injection and multimode ram detonation coupled circulating propulsion system, and particularly relates to a ram detonation engine applied to a space plane power system. The propulsion system has an injection mode (Ma=0-2), a direct shock mode (Ma=2-6) and an oblique shock mode (Ma=6-12) during the detonation process. An annular-phase detonation wave control system of the propulsion system is capable of controlling different modes of a detonation combustion chamber and regulation and switching among the different modes and full propulsion vector regulation of a tail pipe. Propulsion of the propulsion system is increased and can be controlled simultaneously by controlling the detonation flow field through the detonation wave. Rotary detonation thermal circulation and ram power circulation are coupled into the ram detonation power circulation propulsion system structurally and functionally.

Description

1. Technical field [0001] The invention belongs to an air-breathing aviation power system, in particular to a multi-mode ram detonation engine applied to the power system of an aerospace aircraft. 2. Background technology [0002] Under hypersonic conditions, when the incoming air decelerates and enters the combustion chamber, the temperature of the air can rise rapidly due to strong shock wave compression. During the high-static combustion process, a considerable part of the gas molecules absorb energy and are in a state of dissociation, indicating that the chemical energy of combustion is Only a small amount is converted into heat energy, and most of it is converted into dissociation energy. The degree of dissociation is related to the pressure of the gas. When the gas pressure increases, the degree of dissociation will decrease, but the effect of dissociation is always very obvious under hypersonic flight conditions. It is difficult for these dissociation energy to be re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/10F02K1/28F02K1/06
Inventor 董国光
Owner 董国光
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