Fuel-rich pre-burning turbofan engine

Abstract

The invention discloses a fuel-rich pre-burning turbofan engine and relates to an aero-engine technology. An inner duct precooler is located in an inner duct at the back part of an air inlet channel and is located in the upstream position of a fan, and air enters an inner duct of a cooling fan. An outer duct precooler is located in an outer duct at the back part of the air inlet channel and is located in the upstream position of the fan, and air enters an outer duct of the cooling fan. Inner duct air discharged by the fan is continuously compressed in a high-pressure air compressor. The inner duct precooler and the outer duct precooler adopt fuel as cooling media, and fuel heated by the air is mixed in a fuel mixing chamber. The mixed fuel and the air discharged by the high-pressure air compressor are subjected to fuel-rich burning in a gas generator. Fuel-rich gas discharged by the gas generator works in a high-pressure turbine and a low-pressure turbine, and the fan and the high-pressure air compressor are driven to compress the air. The fuel-rich gas discharged by the turbines and outer duct air discharged by the fan are mixed and burnt in an after-burning chamber. High-temperature gas discharged by the after-burning chamber enters an exhaust nozzle to expand to produce thrust force. Thus, the high-specific-impulse and high-Mach-number flight can be realized.

Description

Technical field [0001] The invention relates to the field of aeroengines. It is a high-flying Mach number turbine-based combined cycle engine, more specifically, an afterburner hybrid exhaust turbofan engine with intake pre-cooling and rich combustion pre-combustion. Flying Mach number 4 or more. Background technique [0002] The flight Mach number of the existing air-breathing turbine engine is generally in the range of 1-2, and increasing the flight Mach number to above 4 will significantly shorten the flight time. Because simple cycle engines are difficult to adapt to the large changes in airspace and speed, the turbo-based combined cycle engine propulsion technology has received increasing attention. However, the current turbo ramjet combined engine conceived for high Mach number aircraft has the problems of complex modal conversion and unnecessary quality. The gas generator-type air turbo rocket engine has the problem of low specific impulse, and the expansion air turbo ram...

AI Technical Summary

Problems solved by technology

However, the turbo-ramjet engine currently conceived for high-Mach number aircraft has the problems of complex mode conversion and unnecessary mass, the gas generator-type air-turbine rocket engine has the problem of low specific impulse, and the expansion-type air-turbo-ramjet engine has Low thrust-to-weight ratio and difficult miniaturization, Saber and Scimitar engines have complex structures and difficult matching of components

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