Pulse detonating combustion chamber and air turbine rocket engine based on pulse detonating

A rocket engine and pulse detonation technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., to achieve the effects of weight reduction, high thermal efficiency, and small entropy increase

Pending Publication Date: 2020-06-19
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

However, ATR faces the following key problems in the research, such as the flow matching of high-temperature gas and a

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  • Pulse detonating combustion chamber and air turbine rocket engine based on pulse detonating
  • Pulse detonating combustion chamber and air turbine rocket engine based on pulse detonating
  • Pulse detonating combustion chamber and air turbine rocket engine based on pulse detonating

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Embodiment Construction

[0038] The present invention combines ATR with pulse detonation engine (Pulse Detonation Engine, PDE for short), utilizes the respective advantages and characteristics of PDE and ATR engine, and utilizes pulse detonation combustion chamber (PDC) to replace the ram combustion chamber in the ATR engine , proposed a new concept based pulse detonation air turbine rocket engine (PD-ATR).

[0039] Due to the special structure and working mode of the PD-ATR engine, what enters the detonation combustion chamber is the mixture of the rich combustion gas flowing through the turbine expansion and the compressed air flowing through the compressor, that is, the mixture entering the detonation combustion chamber It is not composed of pure fuel and air according to a certain equivalent ratio, but impure fuel doped with a certain amount of primary combustion products, and has a certain temperature and pressure. It is difficult to use the traditional pulse detonation engine combustion chamber. ...

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Abstract

The invention discloses a pulse detonating combustion chamber and an air turbine rocket engine based on pulse detonating. The pulse detonating combustion chamber adopts an internal jet-flow tube ignition detonating way, and has better efficiency and feasibility in comparison with a transverse heat jet-flow ignition detonating method; internal heat jet-flow ignition is combined with a detonating way of mixing nano particles such as metal aluminum or titanium mixed in fuel oil, so that detonating waves within a relatively short distance and relatively short time can be achieved, and therefore, length of the detonating combustion chamber is shortened, working frequency of an engine is improved, and weight of the engine is reduced. Based on the pulse detonating combustion chamber, the air turbine rocket engine based on pulse detonating disclosed by the invention is improved in parameters such as thrust and specific pulse to certain extent in comparison with those of a conventional ART engine; while an overall pressure ratio of the engine is certain, PDC self-pressurization characteristic can reduce requirements, on pressurization ability of a gas compressor in a PD-ART engine, and grades of rotary parts can be reduced, engine weight is reduced, and therefore, a thrust-weight ratio is increased.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a pulse detonation combustion chamber suitable for impure combustion and an air turbine rocket engine based on pulse detonation. Background technique [0002] Pulse detonation engine (Pulse Detonation Engine, referred to as PDE) is a power device that uses high-temperature and high-pressure gas generated by intermittent or pulse detonation waves to obtain thrust. It has significant advantages such as high thermal efficiency and fast combustion rate. In addition, its The structure is simple, the cost is low, the working range is wide, the application range is wide, and it can work efficiently at subsonic speed and supersonic speed. In addition, due to the self-supercharging characteristics of detonation waves, PDE does not require booster take-off and rotating components such as compressors and turbines, which can save the high-pressure components of traditional turbofan engines, ...

Claims

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Application Information

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IPC IPC(8): F02K9/62F02K7/02
CPCF02K9/62F02K7/02
Inventor 王治武秦为峰张隆飞伟力斯王亚非刘志潘智刚
Owner NORTHWESTERN POLYTECHNICAL UNIV
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