Closed circulating system suitable for aerospace engine

Abstract

The invention relates to a closed circulating system suitable for an aerospace engine. Supercritical state fluid serves as a working medium, and the characteristics that the supercritical state fluid is large in heat capacity, extremely high in heat exchange efficiency, quick in response and low in viscosity are fully utilized so that the whole circulating system can be high in energy transmission capacity and small in flow resistance and can well adapt to changes of working conditions. The system can fully use heat released by cooling of high-temperature inflow air, and comprehensive management of engine energy can be achieved. The closed circulating system is used for the aerospace engine and can overcome defects of an existing engine precooling scheme so that the engine can meet the requirements of a hypersonic aircraft and a single-stage-to-orbit aircraft which can be repeatedly used.

Description

Technical field [0001] The invention relates to a closed cycle system suitable for aerospace engines, and is mainly used for the propulsion system of reusable hypersonic aircraft and single-stage orbiting spacecraft. Background technique [0002] The military and civilian fields have an urgent need for high-speed flight and reducing space launch costs. Reusable hypersonic vehicles and single-stage orbiting spacecraft have become one of the research hotspots in the aerospace field. At present, the main problem that plagues hypersonic flight and single-stage orbit is power. Existing power cannot fully meet the requirements of hypersonic vehicles and single-stage orbiting spacecraft due to their own reasons. The air-breathing engine that pre-cools the incoming air and its combined engine with a rocket engine can overcome the shortcomings of existing power, and is the best power choice for reusable hypersonic aircraft and single-stage orbiting spacecraft . [0003] Existing air-brea...

AI Technical Summary

Problems solved by technology

At present, there are obvious defects in these two precooling measures

The first kind of pre-cooling measures, because the engine needs to carry a large amount of coolant, the weight of the engine is greatly increased. In addition, the large amount of heat released by the cooling of the incoming high-temperature air has not been fully utilized. Distortion, engine length increase and other problems, the performance of the second precooling measure is relatively better, but the current precooler mostly uses fuel as the cooling medium, because the fuel consumption required for cooling is greater than the combustion consumption, resulting in a large amount of fuel being discharged directly In addition, because the cooling system is an open system, the heat absorbed by the fuel from the flowing high-temperature air has not been fully utilized.

Therefore, the specific impulse and thrust-to-weight ratio of the engines using the above two pre-cooling methods are small, which cannot meet the requirements of reusable hypersonic vehicles and single-stage orbiting spacecraft

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