Turbojet propulsion system and control method based on pre-type compression guide impeller

Abstract

The invention provides a turbine jet propulsion system based on a front-mounted compression diversion impeller and a control method thereof. The front-mounted compression diversion impeller is adopted, the pressure ratio of an engine is adjusted, it is achieved that the engine is variable in circulation within the whole envelope range, and the bypass ratio is effectively adjusted, and substantialadjusting and redistribution of inner bypass power and outer bypass power are achieved; and through the design that the engine and an air inlet channel are jointly adjusted, the throat area ratio of the air inlet channel is achieved within the acceptable efficiency range, it is achieved that the air feeding flow rate is matched with the working flow rate of a main machine, thus, the thrust loss isdecreased, and the propulsion efficiency is improved. When the air inflow velocity is low, the compression diversion impeller is used for diversion, a fan is in a small pressure ratio mode, the throat area ratio of the air inlet channel is in the small state, thus, the bypass ratio is effectively increased, and the oil consumption rate is decreased; and when the air inflow velocity is high, the compression diversion impeller is used as a compressor, the throat area ratio of the air inlet channel is in the large state, the pressure ratio of the fan is increased, the bypass ratio is reduced, the turbine front fuel gas temperature is increased, and the specific thrust is improved.

Description

technical field [0001] The present invention relates to the field of aircraft power design, relates to a supersonic aircraft propulsion system, and in particular to a turbojet propulsion system based on a front-mounted compression guide impeller and a control method thereof. In the process, it is possible to take into account the characteristics of large unit thrust of a turbojet engine or a small bypass ratio turbofan engine at supersonic speeds, and the smaller unit thrust, low noise and low noise of a turbofan engine with a large bypass ratio at subsonic speeds. characteristics of fuel consumption. Background technique [0002] The appearance of the turbojet engine has replaced the aviation piston engine, which has greatly improved the flight performance of the aircraft, and human beings have been able to achieve supersonic flight. However, the turbojet engine has superior performance at high speeds and poor economy at low speeds. In order to maintain the better performa...

AI Technical Summary

Problems solved by technology

If the inlet is designed according to a certain higher Ma, the ratio of the throat to the inlet area is relatively small. If it works at a value smaller than the design Ma, the throat area is too small, and the phenomenon of "throat blockage" occurs, which limits the intake air. The air flow in the duct, a normal shock wave appeared in front of the intake duct, resulting in a large overflow loss

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