Rotating disc type aircraft engine

An aero-engine, turntable-type technology, applied to combustion engines, machines/engines, internal combustion piston engines, etc., can solve problems such as waste, insufficient utilization of fuel combustion energy, and large impact force of blades

Inactive Publication Date: 2011-07-20
王仲彦
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, aviation turbofan engines generally adopt the method of burning oil and gas injection to apply impact force to the turbine blades to generate power to drive the intake fan. The impact force on the blades is huge, and the fuel combustion energy cannot be fully utilized. The engine is large in size, difficult to control, serious waste, and safe. Defects such as sex difference

Method used

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  • Rotating disc type aircraft engine

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Embodiment Construction

[0006] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0007] see figure 1 , the present invention provides a rotary disc aero-engine 10 , which includes a cylinder 30 , a rotary disc 50 , a piston 70 connected to the rotary disc 50 and blades 90 . The engine 10 is also provided with a combustion chamber (not shown in the figure), and the combustion chamber is connected to the cylinder block 30 .

[0008] Please also refer to figure 2 , the cylinder body 30 is generally hollow and annular. In this embodiment, the cylinder body 30 is provided with a cylinder wall 301, and the inner circumference of the cylinder wall 301 of the cylinder body 30 is provided with a gap from the horizontal direction, so that the cross-sectional shape of the cylinder body 30 is C-shaped. The cylinder wall 301 encloses a cavity. The cavity 302 of the cylinder body 30 includes an intake cavity 303 , a pressure release...

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Abstract

The invention provides a rotating disc type aircraft engine which comprises a combustion chamber, a cylinder body, a rotating disc, a blade and a piston which is connected to the rotating disc, wherein the cylinder body is of a hollow ring shape and is provided with an air inlet and an air outlet; the piston is contained in the cylinder body; the combustion chamber is connected to the cylinder body and is arranged corresponding to the air inlet of the cylinder body; the combustion chamber is used for inputting and igniting oil gas and applying motive power to the piston; the rotating disc and the blade on the rotating disc are driven by the piston to rotate; and motive power is generated by the rotation of the blade. Compared with the prior art, the rotating disc type aircraft engine provided by the invention has the advantages of scientific and reasonable structure, smaller size, light weight, high energy conversion efficiency, improved rotation speed and improved blade tolerance, is especially applied to the fan motive power of a large turbofan engine with high-bypass ratio, thus fuel can be saved, and the rate of supercharging and push power of the engine can be improved.

Description

technical field [0001] The invention relates to a rotary aero-engine. Background technique [0002] At present, aviation turbofan engines generally adopt the method of burning oil and gas injection to apply impact force to the turbine blades to generate power to drive the intake fan. The impact force on the blades is huge, and the fuel combustion energy cannot be fully utilized. The engine is large in size, difficult to control, serious waste, and safe. Defects such as poor sex. Contents of the invention [0003] In order to overcome the deficiencies of the above-mentioned prior art, the present invention provides a rotary aeroengine, comprising a combustion chamber, a cylinder block, a rotating disk, blades, and a piston connected to the rotating disk. Air port and exhaust port, the piston is accommodated in the cylinder body, the combustion chamber is connected to the cylinder body and set corresponding to the air intake port of the cylinder body, the combustion chamber...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02B53/00F02B55/02F02B55/08
CPCY02T10/17Y02T10/12
Inventor 王仲彦
Owner 王仲彦
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