A small-scale enhanced heat transfer structure

Abstract

The invention provides a small-scale enhanced heat exchange structure which can be used as a sharp end front edge or an air inflow channel overflow port portion of a hypersonic flight vehicle. The structure comprises a skin, a high-heat-conductive structure, an enhanced heat exchange microstructure and an inlet and outlet structure. A heat flow of a local hot spot region can be three-dimensionallyand evenly diffused through the high-heat-conductive structure, meanwhile, the flowing, heat exchange and splitting decomposition processes of a cooling medium are controlled through the enhanced heat exchange microstructure, and full heat exchange is finished in an overflow port region or a sharp end front edge region. The provided enhanced heat exchange structure is simple, reliable in work, low in cost and capable of finishing tasks which cannot be finished though a traditional active cooling technique and broadening the work boundary of the traditional active cooling technique.

Description

technical field [0001] The invention belongs to the field of active thermal protection of hypersonic air inlet overflow port and tip front edge, relates to a small-scale enhanced heat exchange structure, and particularly relates to a hypersonic aircraft tip leading edge or air inlet overflow port The small-scale enhanced heat transfer structure used in the parts. Background technique [0002] For a hypersonic vehicle, the heat entering the interior of each part of the vehicle shows a huge difference due to the huge difference in external aerodynamic heating. The leading edge of the tip, the overflow port, and the combustion chamber are subjected to huge aerodynamic heating or chemical reactions, and the heat flow Density up to 40MW / m 2 , become the main problem to be solved in thermal protection. For the overflow port, considering the profile of the inlet port and the configuration of the wave system, heat protection at the overflow port is required to achieve non-ablation...

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Problems solved by technology

However, the traditional active cooling device is mainly designed for the thermal environment of the engine combustion chamber. The active cooling of the combustion chamber area is a large-area thermal protection, and the heat flux density is 1MW / m 2 , and the main characteristics of the thermal environment in the area of ​​the overflow are that the scale of the local area is small, and the heat flux density distribution of the cold wall is irregular, and the highest point can reach 40MW / m 2 , the heat conduction and convective heat transfer resistance of the wall surface is too large, and hot spots of tens of megawatts will appear. If the active cooling method is adopted, a very large amount of cooling medium is required, but a large amount of cooling medium still cannot reduce the temperature of the overflow port to high temperature. The safe temperature of the alloy is below 1200K, so the traditional active cooling design cannot meet the thermal protection requirements of the overflow

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