Parallel-shaft type aviation gas engine

Abstract

The invention discloses a parallel-shaft type aviation gas engine. An engine system is mainly composed of a compressor and a gas turbine, and the two parts are arranged in a U shape; a gas turbine connected with the compressor is omitted, a heat exchanger is additionally arranged in front of the compressor, a power output shaft drives a compressor shaft through a variable-speed gear or a multistage gearbox, the exhaust temperature and the exhaust speed are both lower than those of a turboshaft engine, and the gas engine is more suitable for being used for vertical take-off and landing airplanes, especially ship-based vertical take-off and landing airplanes, compared with the turboshaft engine; and the double shafts of the engine are arranged in the front of the engine in parallel, two fans can be mounted as well, the thrust power and efficiency of the engine are improved greatly, and the oil consumption is lowered remarkably.

Description

technical field [0001] The invention relates to an aviation gas engine, in particular to a parallel shaft type aviation gas engine. Background technique [0002] At present, twin-shaft aero-engines with free turbines have been widely used in the aviation industry, but the aero-engines of this type widely used in the aviation industry today are either twin-shaft or sleeve-shaft, which is difficult to manufacture, high in production costs, and difficult to lubricate and cool. It is more difficult, either it is a tandem shaft type, the power output shaft is installed at the back of the engine, more is used in the turboshaft engine of the helicopter, and it can also be used in the turboprop engine, and the turbofan engine is rarely used, and whether it is a sleeve shaft Type or tandem shaft type, the exhaust ports are all at the rear of the engine, the engine exhaust is directly discharged into the atmosphere, the exhaust temperature is high, the displacement is large, and the t...

AI Technical Summary

Problems solved by technology

[0002] At present, twin-shaft aero-engines with free turbines have been widely used in the aviation industry, but the aero-engines of this type widely used in the aviation industry today are either twin-shaft or sleeve-shaft, which is difficult to manufacture, high in production costs, and difficult to lubricate and cool. It is more difficult, either it is a tandem shaft type, the power output shaft is installed at the back of the engine, more is used in the turboshaft engine of the helicopter, and it can also be used in the turboprop engine, and the turbofan engine is rarely used, and whether it is a sleeve shaft The exhaust port is at the tail of the engine, the exhaust gas is directly discharged into the atmosphere, the exhaust temperature is high, the displacement is large, and the thermal efficiency of the engine is not high enough

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