Parallel-shaft type aviation gas engine

A gas engine and turboshaft engine technology, which is applied to engine ignition, engine components, gas turbine devices, etc., can solve the problems of high production cost, high exhaust gas temperature, difficult lubrication and cooling, etc., and achieve the effect of simple structure and high strength

Inactive Publication Date: 2017-05-31
袁新友
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  • Abstract
  • Description
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  • Application Information

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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 b

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  • Parallel-shaft type aviation gas engine

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Embodiment Construction

[0011] The present invention will be described in detail below in conjunction with the embodiments and with reference to the accompanying drawings.

[0012] The parallel-axis aviation gas turbofan engine system of the present invention is mainly composed of a compressor and a gas turbine. The compressor consists of a first gear fan (1), a compressor shaft (2), a compressor inlet (13), a compressor machine (11), high-pressure air pipeline (10), the gas turbine is composed of work output gear (5), work output shaft (6), cooling air channel (7), free turbine (8), combustion chamber (9), the first The two-gear fan (3), the dual-purpose DC motor for starting and power generation (4) constitute the auxiliary system for starting and power generation, and the heat exchange exhaust gas channel (12) constitutes the auxiliary heat exchange system. These systems can be arranged on a plane or in a triangular shape Three-dimensional arrangement, the engine can be more compact.

[0013] The...

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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...

Claims

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Application Information

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IPC IPC(8): F02C3/04F02C7/26F01N3/02
CPCF02C3/04F01N3/0205F02C7/26
Inventor 袁新友
Owner 袁新友
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