Cooling scheme for combustion chamber wall surface of aspirated type pulse detonation engine

A technology of pulse detonation and combustion chamber, applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve the problems of insufficient cooling methods, achieve good cooling effect, improve safety, and increase thrust

Inactive Publication Date: 2019-04-05
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] Aiming at the thermal fatigue of the combustion chamber wall of an air-breathing pulse detonation engine and the lack of existing cooling methods, the present invention provides a cooling scheme for the combustion chamber wall of a pulse detonation engine

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  • Cooling scheme for combustion chamber wall surface of aspirated type pulse detonation engine
  • Cooling scheme for combustion chamber wall surface of aspirated type pulse detonation engine
  • Cooling scheme for combustion chamber wall surface of aspirated type pulse detonation engine

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Embodiment Construction

[0025] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0026] The present invention is a cooling solution for the combustion chamber wall of an air-breathing pulse detonation engine, such as figure 2 , image 3 and Figure 4 As shown, it includes: cooling gas inlet 1, detonation tube head 2, fuel inlet 2-1 in the head, combustion chamber air inlet 2-2, detonation tube DDT section 3, sweating hole 3-1 , partition plate with impact hole 3-2, impact hole 3-3, outer casing of the first stage cooling system 3-4, detonation propagation section 4 of the detonation tube, rib plate 4-1, detonation transmission section tube Wall 4-2, tail nozzle 5-1, cooling gas nozzle 5-2.

[0027] The above-mentioned cooling scheme for the combustion chamber wall of an air-breathing pulse detonation engine is characterized in that the present invention consists of a detonation tube, a first-stage cooling system, a second-stage coolin...

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Abstract

The invention provides a cooling scheme for the combustion chamber wall surface of an aspirated type pulse detonation engine. Low-temperature gas of a gas inlet channel is used as a medium, and according to the characteristics of the different temperature of a DDT section and a detonation propagation section of the pulse detonation engine, a zonal cooling method is adopted to cool the combustion chamber wall surface of the aspirated type pulse detonation engine. A shock/sweat combined type cooling method is provided to cool the DDT section with higher temperature in the combustion chamber, thedetonation propagation section with relatively lower temperature is cooled through a method of convective heat exchanging in a channel, and the method of convective heat exchanging in the channel issimple in structure. The thrust of the engine can be improved by making full use of the cooling medium while without carrying an additional cold source. According to the cooling scheme for the combustion chamber wall surface of the aspirated type pulse detonation engine, the problem of uneven temperature distribution caused by existing cooling methods is solved, and the combustion chamber wall surface temperature of the pulse detonation engine is significantly reduced.

Description

technical field [0001] The invention relates to the technical field of pulse detonation engines, in particular to a cooling solution for the combustion chamber wall of an air-breathing pulse detonation engine. Background technique [0002] Pulse Detonation Engine (PDE) is an unsteady propulsion device based on multi-cycle detonation combustion mode. Because the detonation combustion process is similar to the constant volume combustion process, the pulse detonation engine has a higher cycle thermal efficiency than the conventional isobaric combustion engine; on the other hand, the pulse detonation engine can provide a higher pressure ratio, through the Boost to increase the temperature and pressure of the combustible mixture. The pressure of the fuel and oxidant injected into the combustion chamber is relatively low. Compared with the conventional power plant, the complex rotary supercharging parts are omitted, and the structure is simpler, so it can provide a higher thrust-...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/64
CPCF02K9/64
Inventor 范玮贾文杰孙云龙董荣晓张晋
Owner NORTHWESTERN POLYTECHNICAL UNIV
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