Turbine engine

Abstract

The invention provides a turbine engine. The turbine engine comprises a first housing, a second housing, a third housing, a central body, an oil passage assembly, an igniter, a compressor, a turbo machine and a spindle. The first housing has an air inlet. The third housing is fixedly connected to the first housing and the second housing and communicates with the first housing and the second housing. The central body is arranged in the third housing. The outer wall surface of the central body and the inner wall surface of the third housing form a rotary detonation combustion chamber. The oil passage assembly communicates to the rotary detonation combustion chamber in a controllable manner. The igniter is used for igniting combustion gas which is formed by fuel and air entering the rotary detonation combustion chamber such that combustion gas rotates and combusts in a detonation manner. The compressor is used for compressing air entering the first housing through an air inlet. The turbo machine performs rotary motion under the drive of gas in the second housing. The spindle is used for connecting with the compressor and the turbo machine such that the turbo machine drives the compressor to perform motion. The turbine engine has following beneficial effects: the turbine engine is compact in structure and high in combustion efficiency; oil consumption rate of the engine is reduced; and the thrust-weight ratio and the overall performance of the engine are improved.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a turbine engine. Background technique [0002] Thrust-to-weight ratio (the ratio of thrust to engine weight) and fuel consumption rate are important indicators for measuring aviation gas turbine engines, which respectively determine the maneuverability and combat radius (or range) of the aircraft. Due to the limitations of the current material and technological level, it is difficult to further improve the cycle parameters such as the temperature increase ratio and boost ratio of the turbine-based propulsion method, which makes it difficult to continue to increase the thrust of the system. Although the use of afterburners and other methods can make the thrust of the engine The performance has been significantly improved, but the fuel consumption rate of the engine has been greatly increased, so that the combat radius and empty time of the aircraft have been significantly reduced...

AI Technical Summary

Problems solved by technology

Due to the limitations of the current material and technological level, it is difficult to further improve the cycle parameters such as the temperature increase ratio and boost ratio of the turbine-based propulsion method, which makes it difficult to continue to increase the thrust of the system. Although the use of afterburners and other methods can make the thrust of the engine The performance has been significantly improved, but the fuel consumption rate of the engine has been greatly increased, so that the combat radius and air time of the aircraft have been significantly reduced

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