Heat returning closed cooling recirculation system of Brighton scramjet

Abstract

The invention discloses a heating returning closed cooling recirculation system of a Brighton scramjet, which relates to a cooling recirculation system of a scramjet. The invention aims at solving theproblems of cooling difficulty, a large amount of cooling fuel flow, insufficient heat sink and gas-fetching difficulty of the fuel supply system of the scramjet of a prior hypersonic aerial vehicle.One end of a central axis is connected with a generator and another end thereof is respectively connected with a gas compressor and a fuel pump. A turbine is arranged on the central axis between thegenerator and the gas compressor. A cooling channel is arranged on the external wall at the upper part of the scramjet. The cooling recirculation system is provided with a primary cooling loop and a secondary cooling loop. The cooling recirculation system of the scramjet is applicable to the thermal protection of the hypersonic aerial vehicle and the cooling of the scramjet.

Description

Scramjet Regenerative Closed Brayton Cooling Cycle System technical field The invention relates to a cooling cycle system of a scramjet engine. Background technique Hypersonic vehicles with a flying Mach number greater than 5 are a hot topic in current research, including the development of single-stage or two-stage orbital space planes, space-to-ground transport vehicles, and hypersonic cruise missiles. One of the key technologies of the air-breathing hypersonic vehicle with the scramjet engine as the propulsion system is the thermal protection of the vehicle, in which the cooling of the engine is the most difficult part, because even if composite materials are used, it is difficult to withstand the huge heat generated inside the engine. heat load. It is generally believed that fuel is the best coolant, but theoretical analysis and practice show that the coolant flow rate will be greater than the propulsion fuel flow rate after reaching a certain flight Mach number, so e...

AI Technical Summary

Problems solved by technology

The purpose of the present invention is to solve the existing hypersonic vehicle scramjet cooling difficulties, large cooling fuel flow and insufficient heat sink and fuel supply system gas intake difficulties, and proposes a scramjet heat recovery Closed Brayton cooling cycle system

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