Air turbine rocket engine based on pulse detonation

A rocket engine and pulse detonation technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of low total pressure, high temperature, and high airflow velocity, and achieve reduced entropy, fast combustion rate, and high thermal efficiency. Effect

Pending Publication Date: 2020-06-12
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

However, there are also some obvious problems in the ATR engine, such as high air velocity at the inlet of the ram combustion chamber, high temperature, low total pressure, etc.

Method used

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  • Air turbine rocket engine based on pulse detonation
  • Air turbine rocket engine based on pulse detonation
  • Air turbine rocket engine based on pulse detonation

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Embodiment Construction

[0024] The difference between a Pulse Detonation Engine (PDE) and an ordinary engine is that the thrust is generated by the high-temperature and high-pressure gas generated by the pulse detonation wave (about 13-15 times), which allows the engine to run at Mach number 0- 5 has a very wide Mach number range, and can work efficiently at subsonic and supersonic speeds. In addition, detonation combustion has the remarkable advantages of high thermal efficiency (up to 49%) and fast combustion rate (2000m / s). The PDE using this technology has high heat capacity, which can enable the power plant to obtain lower fuel consumption and greater unit thrust.

[0025] The PD-ATR (air turbine rocket engine) proposed by the present invention combines the advantages of high detonation combustion efficiency and self-pressurization with the advantages of high thrust-to-weight ratio, high unit thrust and high unit head-on thrust of traditional ATR engines, and has broad military applications. It...

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Abstract

The invention provides an air turbine rocket engine based on pulse detonation. A pulse detonation combustor is used for replacing a ram combustor in the air turbine rocket engine. The air turbine rocket engine based on the pulse detonation is mainly composed of an air inlet passage, an air compressor, a gas generator, a turbine, a flow mixing and reverse introducing prevention structure, the pulsedetonation combustor and a spray pipe. The gas generator carrying an oxidant and a fuel is arranged in the engine, fuel-rich gas generated by the gas generator drives the turbine to act, the turbinedrives the air compressor to work, air entering from the air inlet passage is compressed by the air compressor and is uniformly mixed with the rich-rich gas acting through the turbine in a flow mixerand then enters the pulse detonation combustor for detonation combustion, and high-temperature high-pressure gas generated by detonation combustion is discharged through the spray pipe to generate thrust; and the detonation combustion has the significant advantages of being high in thermal cycling efficiency, fast in combustion speed, and the like, the air turbine rocket engine based on the pulsedetonation makes full use of the advantages of the detonation combustion, so that a power device obtains lower oil consumption rate and larger unit thrust.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to an air turbine rocket engine based on pulse detonation. Background technique [0002] The Air Turbine Rocket (ATR) is a "hybrid engine" that combines a turbojet engine and a rocket engine. Compared with ordinary turbojet engines, a typical ATR engine has an additional gas generator, which can use its own fuel and oxidant to generate gas, and the oxidant it needs to carry is much smaller than that of a rocket engine. However, there are also some obvious problems in the ATR engine, such as the high air velocity at the inlet of the ram combustion chamber, the high temperature, and the low total pressure. Contents of the invention [0003] At present, there are still some problems in the ATR engine, such as the low total pressure of the inlet airflow of the combustion chamber, especially when flying at high altitude and low Mach number, resulting in a significant decline in combus...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/42F02K9/62
CPCF02K9/42F02K9/62
Inventor 王治武刘志伟力斯王亚非秦为峰张隆飞
Owner NORTHWESTERN POLYTECHNICAL UNIV
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