Variable-cycle air turbine combined engine of rocket

Abstract

The invention discloses a variable-cycle air turbine combined engine of a rocket. The variable-cycle air turbine combined engine of the rocket comprises an axial compressor, a shaft, a main combustion chamber, an air duct, a turbine, an afterburner and an exhaust nozzle, wherein the axial compressor is arranged on the side, with an air inlet, of the main combustion chamber, the turbine is arranged on the side, with an air outlet, of the main combustion chamber, the axial compressor is connected with the turbine through the shaft, the air duct is arranged on the outer side of the main combustion chamber, and is used for communicating the axial compressor with the afterburner, the afterburner is arranged on the exhaust side of the turbine, and the exhaust nozzle is communicated with the afterburner. The variable-cycle air turbine combined engine of the rocket further comprises a fuel gas generator and a second turbine, wherein the fuel gas generator is arranged between the air duct and the main combustion chamber, the second turbine is arranged at the blade tip position of the turbine, and is connected with the axial compressor through the shaft, and an outlet of the fuel gas generator exactly faces the second turbine. The variable-cycle air turbine combined engine of the rocket provides a power system solution scheme for a spacecraft, wherein according to the power system solution scheme, the spacecraft can carry out the long-time economical cruise, and can carry out high-speed maneuver in a short time in a high comprehensive performance mode, and the problem that an existing aviation turbine engine can not carry out self-starting can be solved.

Description

technical field [0001] The invention relates to a variable-cycle air turbine rocket combination engine, which is especially suitable for aeronautical vehicles with low-speed economic cruise for a long time and high-speed maneuvering for a short time. Background technique [0002] At present, the power of aviation aircraft in service mainly includes turbine engine, ramjet engine and rocket engine. These powers have their own advantages and disadvantages: turbine engines have high fuel economy and low thrust-to-weight ratio. Generally, the working height is lower than 20km, and the working speed does not exceed 2Ma; the ramjet engine is suitable for high-altitude and high-speed work, and has good fuel economy, but it cannot start automatically at zero speed. And high-speed maneuvering; the rocket engine can work in the whole airspace and at full speed, but the fuel economy is poor. The single use of these powers is difficult to enable the aircraft to have the ability of long-...

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide an aeronautical vehicle with a power system solution that can not only cruise economically for a long time, but also maneuver at a high speed with higher comprehensive performance in a short period of time, and can solve the problem that the existing aero turbine engine cannot automatically starting problem

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