Active cooling structure and gas-liquid two-phase flow centrifugal spiral enhanced heat transfer method for hypersonic vehicle

Abstract

The invention relates to a hypersonic aerocraft active cooling structure and a gas-liquid two-phase flow centrifugal screw enhanced heat transfer method and belongs to the field of long-term and high-heat-flux local heat transfer in aviation, spaceflight, power machinery and the like. The cooling structure comprises a shock surface, a shock cavity, a jet orifice, a jet flow feeding system and spiral channels. The shock cavity is formed around the shock surface. The shock cavity is communicated with the spiral channels and the jet orifice. The heat transfer method comprises the following steps: the jet flow feeding system jet-impinges a liquid coolant to the shock surface from the jet orifice; the liquid coolant absorbs heat and boils on the surface of the shock surface; a generated gas-liquid two-phase cooling medium flows into the spiral channels and spirally flows along the inner sidewall of a skin to continuously adsorb heat of the skin so as to further boil; and gas-liquid separation is carried out under the action of centrifugal force, and a liquid phase tends to press close to the skin side so as to make bubbles generated on the wall to be rapidly separated from the wall. According to the invention, efficient active cooling of a long-endurance hypersonic aerocraft's nose cone part can be realized, and the cooling efficiency is high. In addition, the aerodynamic configuration of the aircraft will not be damaged, and reliability is high.

Description

technical field [0001] The invention relates to an active cooling structure of a hypersonic vehicle and a gas-liquid two-phase flow centrifugal spiral enhanced heat exchange method, which belongs to the field of local heat exchange with long time and high heat flux density in aviation, aerospace, power machinery, etc. Background technique [0002] Hypersonic aircraft is the main trend in the development of modern aircraft. It has the characteristics of long range, fast speed, and excellent performance. Among them, hypersonic aircraft with a flight speed of Mach 5 to 7, which can fly for a long time and continue to fly, are particularly important. Communication guarantee, intelligence collection, electronic suppression, early warning and other aspects have great potential for development. [0003] However, long-term hypersonic flight will face serious aerodynamic heating problems. When the flight altitude is 24km and the flight speed is Mach 7, the heat flux near the stagnati...

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Problems solved by technology

[0003] However, long-term hypersonic flight will face serious aerodynamic heating problems. When the flight altitude is 24km and the flight speed is Mach 7, the heat flux near the stagnation point of the nose cone is as high as 2-3MW / m 2 , wall temperature up to 1400K

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