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Exhaust chamber inlet side member, exhaust chamber, gas turbine, and last stage turbine blade removal method

An exhaust chamber, inlet side technology, applied in gas turbine devices, blade support elements, engine elements, etc., can solve the problem of inability to take out the last stage turbine moving blades

Active Publication Date: 2016-10-12
MITSUBISHI POWER LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, there is a problem that the last-stage turbine blades interfere with the upstream end of the inner diffuser, and the last-stage turbine blades cannot be removed from the turbine.

Method used

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  • Exhaust chamber inlet side member, exhaust chamber, gas turbine, and last stage turbine blade removal method
  • Exhaust chamber inlet side member, exhaust chamber, gas turbine, and last stage turbine blade removal method
  • Exhaust chamber inlet side member, exhaust chamber, gas turbine, and last stage turbine blade removal method

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Embodiment approach 1

[0076] In this embodiment, a method for removing and taking out the exhaust chamber inlet side member, the exhaust chamber, the gas turbine, and the last-stage turbine rotor blades for detaching the last-stage turbine rotor blades 133 from the turbine disk 104a will be described.

[0077] First, the exhaust chamber inlet side member of the present embodiment will be described. Figure 5 It is a perspective view of an exhaust chamber inlet side member of the gas turbine according to this embodiment.

[0078] Such as figure 2 As shown, the exhaust chamber inlet side member 10 is provided as an upstream end portion of the inner diffuser 5 and is configured to be detachable from the inner diffuser 5 . In the present embodiment, the exhaust chamber inlet side member 10 is a circular cylindrical member formed around the rotor 104 with the axis R as the center. In addition, the exhaust chamber inlet side member 10 is the inlet of the flow of combustion gas (exhaust gas) in the exh...

Embodiment approach 2

[0101] This embodiment is for obtaining the effect that the last-stage turbine rotor blade 133 can be easily removed more remarkably than in the first embodiment described above. Therefore, in the present embodiment, the same reference numerals are assigned to the same parts as those in the above-mentioned first embodiment, and description thereof will be omitted, and only the parts improved from the first embodiment will be described with new reference numerals.

[0102] First, the exhaust chamber inlet side member of the present embodiment will be described. Figure 10 It is a perspective view of an exhaust chamber inlet side member of the gas turbine according to this embodiment.

[0103] The exhaust chamber inlet-side member 10 is annularly formed around the rotor 104 so as to be divided into a plurality of parts in the circumferential direction by a size of the combustion gas passage G between the struts 3 (strut cover 6 ). In this embodiment, the exhaust chamber inlet s...

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Abstract

The purpose is to remove last stage turbine blades easily. That is to say, an exhaust chamber is provided with an exhaust chamber inlet side member (10) that is formed in an annular shape around a rotor (104) so as to form a portion of the interior diffuser (5) in a location facing, on the downstream side in the axial direction, the basal end of the last stage turbine blade (133) disposed furthest downstream in the axial direction, that is separated in the circumferential direction, and that is removably provided with respect to the interior diffuser (5), and when the exhaust chamber inlet side member is released from the interior diffuser (5), a space is formed on the downstream side in the axial direction of each last stage turbine blade (133).

Description

technical field [0001] The invention relates to an inlet side member of an exhaust chamber of a gas turbine, an exhaust chamber of the gas turbine, a gas turbine and a method for taking out the last-stage turbine moving blade of the gas turbine. Background technique [0002] A gas turbine consists of a compressor, a combustor, and a turbine. The compressor forms high-temperature, high-pressure compressed air by compressing the air introduced from the air inlet. The combustor forms high-temperature, high-pressure combustion gas by supplying fuel to compressed air and burning it. The turbine is configured by alternately arranging a plurality of turbine stator blades and turbine rotor blades in passages in the casing, and the turbine rotor blades are driven by the combustion gas supplied to the passages, thereby driving the rotor (rotary shaft) connected to the generator and make it rotate. The combustion gas that drives the turbine is discharged to the atmosphere as exhaust...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D25/30F01D25/24F02C7/00
CPCF01D9/041F01D25/162F01D25/243F01D25/30F05D2220/3215F05D2230/70F01D5/02F01D5/12F01D9/02F01D25/24F02C3/04F05D2220/32F05D2240/35F05D2240/60
Inventor 桥本拓郎胁邦彦桥本真也
Owner MITSUBISHI POWER LTD
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