Methane precooling turbine-based combined cycle engine system with interstage combustion chamber

Abstract

The invention provides a methane precooling turbine-based combined cycle engine system with an interstage combustion chamber, which is characterized in that a liquid methane precooling heat exchanger device is additionally arranged in front of a gas compressor of a turbine main engine, and liquid methane with high latent heat is used for cooling high-temperature gas flow from a gas inlet channel, so that a compression system stably works to maintain high Ma flight of the engine; after the liquid methane is adopted to precool high-temperature air flow in the air inlet channel, the reduced rotating speed working range of a compression system is effectively reduced, the stable working margin of the compression system is improved, meanwhile, interstage combustion of a turbine engine is started, the effective cycle work of the engine is greatly increased, the unit thrust is improved, and the maximum flight Ma of the engine is expanded to 3.5. After the flight Ma is increased to 3.5, the working condition of the scramjet engine is met, the scramjet engine is started, the aircraft is pushed to Ma5 +, at the moment, the turbine engine can be gradually closed, and only the scramjet engine is started for flight.

Description

technical field [0001] The invention relates to the field of aircraft power design, relates to a supersonic aircraft power system, in particular to a methane precooling turbine-based combined cycle engine system with an interstage combustion chamber. Background technique [0002] The United States has mainly studied jet precooling turbine engines since the 1950s. In 2002, the U.S. Defense Advanced Research Projects Agency (DARPA) proposed the Rapid Response Small Load Low-Cost Carrier (RASCAL) program, which took the jet pre-cooling technology as one of the key research contents, and completed the simulation of the engine ground under high altitude conditions on the F100 engine. Test verification of liquid oxygen and water jet pre-cooling technology for intake air heating. The flight platform equipped with the F100 engine must carry a device for storing liquid oxygen and water, which greatly reduces the thrust-to-weight ratio of the aircraft, and the expansion of the flight...

AI Technical Summary

Problems solved by technology

When water jet precooling is used, a large amount of water, oxidant or volatile agent needs to be carried. The problem of "dead weight" is difficult to solve, which greatly increases the weight of the aircraft, reduces the thrust-to-weight ratio of the aircraft, and can only work at supersonic speed for a period of time. It is currently in the demonstration stage.

The technical route of using other precoolants or devices to increase engine thrust and expand engine flight envelope is still in the stage of numerical simulation

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