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Power rear output type turboprop engine and aircraft

A turbo propeller and power output technology, which is applied in the direction of machines/engines, gas turbine devices, mechanical equipment, etc., can solve the problems of large air intake loss, large outline size, and large aerodynamic resistance, so as to reduce air intake loss and improve structural layout Compactness, the effect of reducing the weight of the whole machine

Active Publication Date: 2021-07-02
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The invention provides a power rear output turboprop engine and an aircraft to solve the technical problems of the existing turboprop engine with large outline size, large windward area and large aerodynamic resistance and large air intake loss

Method used

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  • Power rear output type turboprop engine and aircraft
  • Power rear output type turboprop engine and aircraft

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Embodiment Construction

[0026] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0027] figure 1 It is a structural schematic diagram of a power rear output turboprop engine in a preferred embodiment of the present invention; figure 2 It is a structural schematic diagram of a power rear output turboprop engine in a preferred embodiment of the present invention.

[0028] Such as Figure 1-2 As shown, the power rear output turboprop engine of this embodiment is used to transmit power to the thrust output device to push the aircraft forward, and includes an accessory transmission device 6 arranged sequentially along the axial direction of the power rear output turboprop engine, Air intake device 1, gas generating device 2, exhaust device 4, power output device 3 installed on the inside of the intake end of exhaust device 4 for extracting power...

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Abstract

The invention discloses a power rear output type turboprop engine. The engine comprises an accessory transmission device, a gas inlet device, a fuel gas generation device and a gas exhaust device which are sequentially arranged in the axial direction, a power output device mounted on the inner side of the gas inlet end of the gas exhaust device and used for extracting power from high-temperature and high-pressure fuel gas exhausted by the fuel gas generation device, as well as a speed reduction transmission device which extends from the gas exhaust end of the gas exhaust device in the axial direction, is connected with the power output device and is used for transmitting power to a thrust output device; the air inlet device is provided with an air inlet flow channel used for leading air into the fuel gas generating device, and the air inlet flow channel extends inwards in the radial direction of the power rear output type turboprop engine and then bends and extends to the air inlet end of the fuel gas generating device; the gas exhaust device is provided with a gas exhaust flow channel used for gas exhausting fuel gas flowing through the power output device and a gas exhaust port communicating with the gas exhaust flow channel, and the gas exhaust flow channel extends outwards to the gas exhaust port in the radial direction of the rear power output type turboprop engine after being bent and extending.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a power-rear output turboprop engine and an aircraft. Background technique [0002] Gas turbine engines have developed various structural forms such as turbojet engines, turbofan engines, and turboprop engines, and are widely used to provide power for military and civilian aircraft. Compared with the turbojet turbofan engine, the turboprop engine has the advantages of economy, fuel economy and good low-speed characteristics, and is widely used in small and medium-sized transport aircraft and general aviation aircraft. [0003] For a turboprop engine, air enters the engine and is compressed by the compressor, and then mixed with fuel in the combustion chamber to generate high-temperature and high-pressure gas. A gas turbine connected to the compressor extracts energy from the gas to drive the compressor to continue to rotate. The gas turbine can drive the propeller to rotate...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C6/20F02C7/36F02C3/04
CPCF02C6/206F02C7/36F02C3/04
Inventor 石建成肖华中吴谋彬
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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