Ram air turbine thermoelectric conversion and pre-cooling method for turbine based combined cycle

Abstract

The invention provides a ram air turbine thermoelectric conversion and pre-cooling method for a turbine based combined cycle and relates to a combined engine. By the adoption of the ram air turbine thermoelectric conversion and pre-cooling method for the turbine based combined cycle, the power supply requirement of an aircraft of the combined engine is met when the flight match number is high, the purpose that the air flow of an air intake channel of a turbine engine is pre-cooled when the flight match number is high is achieved, the structure is simple, the air intake is adjustable, and the overflow resistance of an air intake channel of a scramjet engine can be reduced. When the flight mach number reaches 2, the turbine engine starts to be gradually closed, the air intake channel of the scramjet engine is opened, and the scramjet engine starts to work; and when the air intake channel of the turbine engine is closed completely, the turbine engine is completely closed. By the adoption of the method, the defect that the power supply of the aircraft is insufficient when an existing combined engine flies at the hypersonic speed is overcome, and the problem that the temperature of the airflow before a turbine engine gas compressor is too high when the turbine engine and the scramjet engine work at the same time is solved.

Description

technical field [0001] The invention relates to the field of combined engines, in particular to a ram air turbine thermoelectric conversion and precooling method of a turbo ram jet combined engine. Background technique [0002] The power system of a wide-speed aircraft not only requires the ability to freely enter the adjacent space, but also requires the ability to cruise at high altitude at high speed. Other characteristics such as reusability and wide adaptable speed range. Existing aero-engines, rocket engines and ramjet engines are difficult to meet the above requirements due to their own technical reasons. [0003] By combining the existing mature power devices, realizing the autonomous flight of the aircraft in a wide speed range has become a research hotspot in the aviation and military powers in recent years, and it is also one of the important directions in the field of aerospace research in my country. The combined cycle engine consists of a turbine-based engine...

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Problems solved by technology

[0005] The purpose of the present invention is to solve the problems of insufficient power supply of the aircraft when the existing combination engine is flying at hypersonic speed, and the excessive temperature of the airflow before the compressor of the turbine engine when the turbine engine and the ramjet engine are working at the same time, and provide a combination engine that can meet the requirements of high Mach number flight. Power supply requirements of the engine aircraft and the purpose of air precooling of the air inlet of the turbine engine. The structure is simple, and the intake air volume can be adjusted. It can also reduce the overflow resistance of the inlet of the ramjet engine. The turbo ramjet combination engine ram air turbine thermoelectric conversion and Pre-cooling method

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