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Static stamping gas turbine, and using method and application thereof

A gas turbine and turbine technology, applied in the field of mechanical power, can solve the problems of uneven mixing of air and fuel, low air compression rate, etc., and achieve the effect of excellent mixing effect, high compression ratio, and improved compression ratio

Pending Publication Date: 2018-08-10
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 static ram gas turbine has a fixed structure, the mixing of air and fuel is uneven, and the air compression rate is low, the present invention provides a static ram gas turbine, which adopts a rotor structure and has a high air compression ratio. Evenly mixed, the static ram gas turbine of the present invention has high effective efficiency

Method used

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  • Static stamping gas turbine, and using method and application thereof
  • Static stamping gas turbine, and using method and application thereof
  • Static stamping gas turbine, and using method and application thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0095] A static ram gas turbine, the engine consists of a compressor and combustion rotor assembly 1, an intake guide 2, a tail spray cover 3, a turbine 8 and a transmission shaft 9. 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 ig...

Embodiment 2

[0097] Repeat Example 1, except that the engine also includes two helical guide oil pressure devices 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 . One of the helical guide oil presses 4 is arranged between the rotating shaft 101 and the ceramic bearing 204 with oil holes, and one helical guide oil press 4 is arranged between the top of the ceramic bearing 204 with oil holes and the fuel steering cap 5 . The fuel diverting cap 5 is arranged on the top of the bearing sleeve 201 and is sealedly connected with the bearing sleeve 20...

Embodiment 3

[0099] Embodiment 2 is repeated, except that the air intake guide 2 is provided with a top air intake 205 and a side air intake 206 . The top air inlet 205 is provided with a longitudinal air inlet guide piece 20501 . The side air inlet 206 is provided with a radial air inlet guide piece 20601 .

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Abstract

The invention provides a static stamping gas turbine. An engine comprises a compressed gas and combustion rotor assembly, an air inlet guiding device, a tail-jet hood, a turbine and a transmission shaft; the compressed air and combustion rotor assembly comprises a rotating shaft, a rotational flow compressed air spiral channel, an air inlet, a diffusion combustion air outlet, an oil nozzle and a combustion igniter. The rotational flow compressed air spiral channel is of a pipeline structure. The air inlet guiding device is internally provided with a bearing sleeve, and the rotating shaft penetrates through the bearing sleeve and is in matched connection with the bearing sleeve. The turbine is arranged at the tail end of the diffusion combustion air outlet and located in the tail-jet hood;one end of the transmission shaft is fixedly connected with the turbine; and the other end of the transmission shaft sequentially penetrates through a transmission shaft of the compressed air and combustion rotor assembly and the air inlet guiding device and stretches out of the upper surface of the air inlet guiding device. The engine adopts a rotor structure, the air compression ratio is high, and air and fuel are mixed evenly.

Description

technical field [0001] The invention relates to an engine, in particular to a static ram gas turbine 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 flows out...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C3/045F02C7/057F02C7/00
CPCF02C3/045F02C7/00F02C7/057
Inventor 朱振武陈豪湘朱志胤
Owner 朱志胤
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