Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof

A ramjet, regenerative cooling technology, applied in ramjet engines, mechanical equipment, etc., can solve problems such as difficulty in cooling, achieve sufficient combustion, high combustion efficiency, expand the applicable flight Mach number and effectively stabilize the working range.

Active Publication Date: 2014-03-12
INST OF MECHANICS - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0004] Aiming at the cooling difficulty of the subsonic combustion ramjet engine at a higher flight Mach number, and overcoming the deficiencies of the existing passive thermal protection method for the subsonic

Method used

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  • Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof
  • Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof
  • Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof

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Embodiment Construction

[0026] Hereinafter, the embodiments of the present invention will be described in detail with reference to the accompanying drawings. It should be noted that the embodiments in the application and the features in the embodiments can be combined with each other arbitrarily if there is no conflict.

[0027] The invention proposes a subsonic combustion ramjet combustion chamber with a regenerative cooling structure, and a method for regeneratively active cooling of the subsonic combustion ramjet combustion chamber using airborne hydrocarbon fuel. Through preliminary tests on a set of quantitatively designed cooling structure engine combustion chambers, the feasibility of this cooling method is preliminarily verified. In a nutshell, the cooling method is a method of injecting the engine's hydrocarbon fuel into the combustion chamber to generate thrust before it flows through the cooling structure covering the surface of the engine's combustion chamber for efficient thermal protection...

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Abstract

The invention discloses a subsonic velocity combustion ramjet combustion chamber and a regenerative cooling method of the subsonic velocity combustion ramjet combustion chamber. The subsonic velocity combustion ramjet combustion chamber comprises an air inlet segment, a combustion segment and a spray pipe segment. A regenerative cooling structure is arranged inside an outer shell of the combustion segment and the spray pipe segment. The regenerative cooling structure comprises multiple cooling channels. Hydrocarbon fuel cools the combustion chamber through the cooling channels first, and then enters the combustion chamber for combustion. By means of the regenerative cooling method and the cooling structure, the temperature of an engine body can be lowered greatly to be below the allowable temperature of an engine manufacturing material, thermal balance of a whole system can be realized quickly, and therefore the effect of long-time effective thermal protection of the subsonic velocity combustion ramjet combustion chamber is achieved; moreover, the fuel after absorbing heat is higher in combustion efficiency and sufficient in combustion, and therefore the thrust and endurance of a subsonic velocity combustion ramjet can be effectively increased.

Description

Technical field [0001] The invention relates to the field of subsonic combustion ramjet engines, in particular to a subsonic combustion ramjet combustion chamber and a regeneration cooling method thereof. Background technique [0002] The cooling of subsonic combustion ramjet engines with a flying Mach number greater than 2.5 and less than 5 is one of the core challenges for designing high-efficiency high-speed aircraft in this speed range. An excellent comprehensive thermal management method should not only achieve long-term effective cooling and thermal protection of high-speed aircraft to achieve long-distance use, but also hope to improve fuel combustion efficiency to increase aircraft engine thrust and further enhance its endurance. The role of. [0003] However, currently common aircraft using sub-combustion ramjet engines use the heat absorption process of high-temperature thermal protection materials to cool the aircraft fuselage. On the one hand, this kind of passive the...

Claims

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Application Information

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IPC IPC(8): F02K7/10
Inventor 陆阳袁涛李龙王新竹王晶司徒明范学军
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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