Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof

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...

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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 combustion ramjet combustion chamber, the present invention proposes a subsonic combustion ramjet combustion chamber and its regenerative cooling method to meet the requirements of sub-combustion ramjet aircraft

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