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Gas turbine stationary blade with flow guide pipe

A technology of gas turbines and draft tubes, applied in mechanical equipment, engine components, machines/engines, etc., can solve problems such as inability to arrange, achieve efficient and reasonable structural design, enhance convective cooling and impact cooling effects, and reduce casting difficulty.

Pending Publication Date: 2022-02-25
浙江燃创透平机械有限公司 +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to solve the technical problem that the traditional guide tube cannot be arranged in the narrow channel at the blade tail due to technological limitations, the present invention provides a gas turbine stator blade with a guide tube

Method used

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  • Gas turbine stationary blade with flow guide pipe
  • Gas turbine stationary blade with flow guide pipe
  • Gas turbine stationary blade with flow guide pipe

Examples

Experimental program
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Effect test

Embodiment 1

[0035] according to Figure 1-Figure 5 A gas turbine vane 2 with a draft tube is shown, including a front cavity 13, a middle cavity 14 and a rear cavity 3; the front cavity 13, the middle cavity 14 and the rear cavity 3 are arranged in sequence, and the front cavity 13, The middle cavity 14 and the rear cavity 3 are set independently of each other, and the front cavity 13, the middle cavity 14 and the rear cavity 3 respectively form air cooling passages inside the vane 2; and the rear cavity 3 is provided with an air supply cavity 5;

[0036] The vane 2 also includes a guide tube 1, the guide tube 1 is arranged inside the rear cavity 3, and an annular channel 4 is formed between the periphery of the guide tube 1 and the wall surface of the rear cavity 3, the guide tube 1 surrounds the air supply chamber 5, wherein the air supply chamber 5 and the annular channel 4 are communicated through the impact hole 6 opened on the draft tube 1; the purpose of setting the impact hole 6 i...

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PUM

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Abstract

The invention discloses a gas turbine stationary blade with a flow guide pipe, which relates to the field of gas turbines and comprises a front cavity, a middle cavity, a rear cavity and the flow guide pipe, wherein the front cavity, the middle cavity and the rear cavity are sequentially arranged, an air supply cavity is formed in the rear cavity, the flow guide pipe is arranged in the rear cavity, an annular channel is formed between the flow guide pipe and the wall surface of the rear cavity, the flow guide pipe surrounds the air supply cavity, and an impact hole communicating the annular channel and the air supply cavity is formed in the flow guide pipe; the flow guide pipe comprises a folded plate assembly, and the folded plate assembly comprises a first folded plate, a second folded plate and a third folded plate; in the direction close to the tail of the rear cavity, the distance between the first folded plate and the inner wall surface of the stationary blade suction surface is reduced; the distance between the second folded plate and the inner wall surface of the stationary blade pressure surface is reduced; and the distance between the third folded plate and the inner wall surface of the stationary blade pressure surface is reduced. The flow guide pipe has a reinforced cooling effect on the inner wall surface of a narrow channel at the tail of the blade, high-temperature oxidation corrosion of the area is prevented, and the service life of the blade is prolonged.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a gas turbine stationary blade with a draft tube. Background technique [0002] Considering the thermal cycle of a gas turbine, increasing the gas temperature before the turbine is fundamental to improving the thermal efficiency and power of the whole machine. As the performance requirements of gas turbines are getting higher and higher, the gas temperature at the inlet of the turbine is also getting higher and higher. At present, the inlet temperature of mainstream gas turbine turbines far exceeds the high temperature resistance of the turbine blade itself. Reasonable introduction of cooling system is the key to solving the problem. . Efficient cooling technology can prolong the service life of heated components and use more economical materials to reduce costs. These remarkable advantages make the design of cooling system play a pivotal role in the development of high-per...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D9/06F01D25/12
CPCF01D9/02F01D9/06F01D25/12
Inventor 周灵敏吴宏超隋永枫王博蓝吉兵韩先洪初鹏任晟
Owner 浙江燃创透平机械有限公司