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Sealing structure

A technology of sealing structure and sealing components, which is applied in the directions of engine sealing, engine cooling, engine function, etc. It can solve the problems of damage to the heat-resistant coating and narrowing of the gap, and achieve the effect of preventing damage

Active Publication Date: 2017-05-17
MITSUBISHI POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the gap between adjacent parts is narrowed due to the difference in thermal elongation, and the opposing side wall surfaces may come into contact with each other, resulting in peeling of the heat-resistant coating material and damage to the heat-resistant coating.

Method used

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Experimental program
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no. 1 approach 》

[0036] Below, refer to Figure 1 to Figure 6 , the first embodiment of the present invention will be described.

[0037] Such as figure 1 and figure 2 As shown, the gas turbine 1 includes a compressor 10 that compresses external air to generate compressed air A, a plurality of combustors 20 that mix and burn fuel and compressed air A to generate combustion gas G, and a turbine driven by the combustion gas G. 30.

[0038] The turbine 30 includes a casing 31 and a turbine rotor 33 that rotates about a rotor axis Ar within the casing 31 . The turbine rotor 33 is, for example, connected to a generator (not shown) that generates electricity by the rotation of the turbine rotor 33 .

[0039] The compressor 10 is arranged on the side of the rotor axis Ar with respect to the turbine 30 . The casing 31 of the turbine 30 has a cylindrical shape centered on the rotor axis Ar. In the compressor 10 , a part of the compressed air A is supplied to the turbine 30 and the combustor 20 a...

no. 2 approach 》

[0111] Next, refer to Figure 7 and Figure 8 , the sealing structure 200 of the second embodiment will be described.

[0112] In the second embodiment, the same reference numerals are attached to the same constituent elements as those in the first embodiment, and detailed description thereof will be omitted. The sealing structure 200 of the second embodiment is different from the first embodiment in that the sealing structure 200 is formed on the segment rings 60 adjacent in the circumferential direction Dc.

[0113] Hereinafter, a sealing structure 200 according to a second embodiment of the present invention will be described. Figure 7 The cross-sectional structure of the segment ring 60 viewed from the circumferential direction Dc is shown. Figure 8 A cross-sectional structure of the segment ring 60 viewed from the rotor axial direction Da is shown.

[0114] The seal structure 200 of the second embodiment is used for the segment rings 60 adjacent in the circumferenti...

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Abstract

A sealing structure comprises: a first member disposed to face a combustion gas channel; a second member; a third member disposed on the outside of the combustion gas channel; a heat resistant covering portion formed on the combustion gas channel side on at least one of a first end face and a second end face; and a contacting portion disposed on the first end face and the second end face further to the outside than the heat resistant covering portion. When the first member and the second member move relative to each other in a direction to become closer, the contacting portion restricts the relative motion by being in contact with said members with a gap formed between the heat resistant covering portion and the opposing face.

Description

technical field [0001] The invention relates to a sealing structure. [0002] this application claims priority based on Japanese Patent Application No. 2014-196771 for which it applied on September 26, 2014, and uses the content here. Background technique [0003] In a gas turbine, air pressurized by a compressor is mixed with fuel in a combustor to generate combustion gas as a high-temperature fluid, and the combustion gas is sent to a turbine in which stationary blades and moving blades are alternately arranged. Introduced into the flow path. In the gas turbine, the rotor blades and the rotor are rotated by the combustion gas flowing through the combustion gas flow path. Thereby, the gas turbine outputs the energy of the combustion gas as rotational energy, and imparts rotational driving force to the compressor and the generator. [0004] A gap is provided between the transition piece of the combustor and the shroud of the first-stage stator vane of the turbine to preve...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/28F02C7/18F01D11/00F16J15/06
CPCF02C7/28F05D2230/31F01D9/023F01D11/005F01D25/12F16J15/162F16J15/4476F05D2240/11F05D2260/201F01D11/00F02C7/18F16J15/06F01D11/003F01D11/10F01D25/24
Inventor 近藤隆博桥本真也谷口健太
Owner MITSUBISHI POWER LTD