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Geostationary stamping aerospace engine and use method and application thereof

An aerospace and engine technology, applied in the field of mechanical power, can solve the problems of low air compression rate, uneven mixing of air and fuel, etc., achieve high compression ratio, excellent mixing effect, and improve the effect of compression ratio

Pending Publication Date: 2018-08-07
朱志胤
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Aiming at the defects in the prior art that the ramjet engine is a fixed structure, the air and fuel are not mixed uniformly, and the air compression rate is low, the present invention provides a static ramjet aerospace engine, which adopts a rotor structure, has a high air compression ratio, and the air and fuel Evenly mixed, the effective efficiency of the hydrostatic ram aerospace engine of the present invention is high

Method used

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  • Geostationary stamping aerospace engine and use method and application thereof
  • Geostationary stamping aerospace engine and use method and application thereof
  • Geostationary stamping aerospace engine and use method and application thereof

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Embodiment approach

[0064] According to the first embodiment provided by the present invention, a static ram jet aerospace engine is provided.

[0065] A static ram jet aerospace engine is composed of a compressed air and combustion rotor assembly 1, an air intake guide 2, and a tail spray cover 3. The compressed gas and combustion rotor assembly 1 includes a rotating shaft 101 , a swirl compressed gas spiral passage 102 , an air inlet 103 , a diffused combustion gas outlet 104 , a fuel injector 105 , and a combustion igniter 106 . The swirling flow and compressed air spiral channel 102 is a pipeline structure. The swirl flow and compressed air spiral channel 102 is arranged on the outside of the rotating shaft 101 in a spiral shape. The top of the swirl air compressor spiral channel 102 is an air inlet 103 . The end of the swirl-flow compressed gas spiral channel 102 is a diffuser combustion gas outlet 104 . The fuel injection nozzle 105 is arranged on the inner sidewall of the swirl air comp...

Embodiment 1

[0088] A static ram jet aerospace engine is composed of a compressed air and combustion rotor assembly 1, an air intake guide 2, and a tail spray cover 3. The compressed gas and combustion rotor assembly 1 includes a rotating shaft 101 , a swirl compressed gas spiral channel 102 , an air inlet 103 , a diffuser combustion gas outlet 104 , a fuel injector 105 , and a combustion igniter 106 . The swirling flow and compressed air spiral channel 102 is a pipeline structure. The swirl flow and compressed air spiral channel 102 is arranged on the outside of the rotating shaft 101 in a spiral shape. The top of the swirl air compressor spiral channel 102 is an air inlet 103 . The end of the swirl-flow compressed gas spiral channel 102 is a diffuser combustion gas outlet 104 . The fuel injection nozzle 105 is arranged on the inner sidewall of the swirl air compressor spiral channel 102 and is located at the position of the air inlet 103 . The combustion igniter 106 is arranged on the...

Embodiment 2

[0090] Embodiment 1 is repeated, except that the engine also includes a screw guide oil pressure device 4 and a fuel steering cap 5 . An oil delivery pipe 202 is provided on the intake guide 2 . The bearing sleeve 201 is provided with a solid ceramic bearing 203 and a ceramic bearing 204 with oil holes. The top end of the rotating shaft 101 passes through the solid ceramic bearing 203 and the ceramic bearing 204 with oil holes in sequence. The oil delivery pipe 202 is connected with the ceramic bearing with oil holes 204 and communicates with the oil hole in the ceramic bearing with oil holes 204 . The screw guide oil presser 4 is arranged between the rotating shaft 101 and the ceramic bearing 204 with oil holes. The fuel diverting cap 5 is arranged on the top of the bearing sleeve 201 and is sealedly connected with the bearing sleeve 201 . The top of the rotating shaft 101 is provided with an oil inlet hole 10101 , and the inside of the rotating shaft 101 is provided with ...

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Abstract

Provided is a geostationary stamping aerospace engine. The engine comprises an air injection and combustion rotor assembly, an air inlet guider and a tail jet cover. The air injection and combustion rotor assembly comprises a rotating shaft, a rotational flow air injection spiral channel, an air inlet, a diffusion combustion air outlet, an oil spraying nozzle and a combustion igniter. The rotational flow air injection spiral channel is of a pipeline structure and is spirally arranged outside the rotating shaft. The air inlet is formed in the top of the rotational flow air injection spiral channel, and the diffusion combustion air outlet is formed in the tail end of the rotational flow air injection spiral channel. The oil spraying nozzle is arranged on the inner side wall of the rotationalflow air injection spiral channel and located at the air inlet. The combustion igniter is arranged at the inner center of the rotational flow air injection spiral channel and located at the diffusioncombustion air outlet. A bearing bush is arranged in the air inlet guider. The rotating shaft penetrates through the bearing bush and is matched and connected with the bearing bush. According to thestamping engine, by means of a rotor structure, the air compression ratio is high, air and fuel are evenly mixed, and efficiency is high.

Description

technical field [0001] The invention relates to an engine, in particular to a static ram aerospace engine and its use method and application, belonging to the field of mechanical power. Background technique [0002] Compressor: A component in a gas turbine engine that uses high-speed rotating blades to work on the air to increase the air pressure. Compressors can be divided into two categories: centrifugal and axial flow. Centrifugal compressors are composed of wind deflectors, impellers, and diffusers. The air enters the compressor from the air inlet, and is guided by the wind deflector that rotates together with the impeller and enters the impeller. Under the action of the high-speed rotating impeller, the air is thrown from the center of the impeller to the outer edge of the impeller by centrifugal force, and the pressure gradually increases. After the air flowing out of the impeller enters the diffuser, the speed decreases, the pressure increases again, and finally flow...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/16
CPCF02K7/16
Inventor 朱振武朱志胤
Owner 朱志胤
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