Separate-exhaust air turbine rocket combined propulsion system

Abstract

The invention relates to a separate-exhaust air turbine rocket combined propelling system which comprises a core engine of an air turbine rocket engine, the core engine is composed of a rocket gas generator, a turbine and a gas compressor, and the turbine and the gas compressor are coaxially arranged. The rocket fuel gas generator is connected with the rocket fuel conveying device, rich fuel gas generated when the rocket fuel gas generator works drives the turbine to drive the gas compressor, the gas compressor sucks air and pressurizes the air, and the pressurized air directly enters the first combustion chamber and burns with fuel sprayed into the first combustion chamber in the first combustion chamber to release heat. The fuel gas expands through the outer spray pipe to do work to generate thrust; meanwhile, the fuel gas behind the turbine enters the second combustion chamber to be combusted and then is directly sprayed out of the inner spraying pipe to generate thrust. The problem that the pressure intensity of a fuel gas generator is high can be solved, traditional fuel gas and air mixing is replaced, and the working speed range of an engine is widened.

Description

technical field [0001] The invention relates to an air-breathing propulsion system, in particular to an air turbine rocket combined propulsion system. Background technique [0002] With the pursuit of speed by human beings, the working range of the engine is getting wider and wider, and the aircraft has higher and higher requirements for the engine, such as wide speed range, zero-speed start, and good performance. This requires improving the adaptability of the engine to different speeds. In 1932, Goddard, the father of American rockets, proposed the Air Turbine Rocket Engine (ATR). As an engine with a relatively wide speed range, it has certain applications in missiles. As an engine working in Ma0-Ma3, it may not be able to meet the current wide range of working conditions. The main reason is that when the engine gas generator works at high Mach, the chamber pressure of the gas generator is too high, which makes the engine design more difficult. This overpressure problem ...

AI Technical Summary

Problems solved by technology

But in essence, it does not solve the problem of high pressure in the gas generator of the ATR engine

[0006] The air-breathing turbo rocket engine or its modification has the problem of too high pressure of the gas generator, which seriously affects the working speed range of the engine. At the same time, the high pressure increases the difficulty of manufacturing, and there is currently no separate exhaust gas Dissertations and Dissertations on ATR Propulsion Systems

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