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Platform segment for supporting a nozzle guide vane for a gas turbine and method of cooling thereof

A gas turbine, guide vane technology, applied in mechanical equipment, engine components, engine functions, etc., can solve the problems of material oxidation, limit the working life of the platform, etc., to achieve the effect of enhancing turbulence

Inactive Publication Date: 2013-02-27
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Specifically, impingement gases can cause severe oxidation of the materials contained within the platforms used to support the nozzle guide vanes
Therefore, it will limit the operating life of the platform

Method used

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  • Platform segment for supporting a nozzle guide vane for a gas turbine and method of cooling thereof
  • Platform segment for supporting a nozzle guide vane for a gas turbine and method of cooling thereof
  • Platform segment for supporting a nozzle guide vane for a gas turbine and method of cooling thereof

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Embodiment Construction

[0052] The illustrations in the figures are schematic. It should be noted that in different figures, similar or identical elements have the same reference signs or reference signs that differ only in the first order from the corresponding reference signs.

[0053] figure 1 Schematically shows a cross-sectional view of a portion of a gas turbine comprising a radially outer platform segment 100 for supporting nozzle guide vanes according to an embodiment and a radially inner platform segment for supporting nozzle guide vanes according to an embodiment. Platform segment 150 . The working gas exhausted from the burners upstream of the outer platform segment 100 and the inner platform segment 150 propagates in a direction indicated by reference numeral 101 . The unmarked axis of rotation lies along the horizontal orientation of the figure 1 within the drawing plane.

[0054] By the direction 101 of the flowing or circulating working gas, the upstream side of a component of the ...

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Abstract

It is described a platform segment for supporting a nozzle guide vane for a gas turbine, the platform segment comprising: a gas passage surface (117, 119) arranged to be in contact with a streaming gas exhausted from a combustor, wherein the streaming gas streams along the gas passage surface in a streaming direction (101); a cooling surface (131, 149) opposite to and thermally connected to the gas passage surface and arranged to be in contact with a cooling fluid; a wall (133, 151) protruding from the cooling surface and extending at least partially in the streaming direction (101), wherein the wall is arranged circumferentially between positions, at which adjacent guide vanes are to be provided, such that cooling fluid is channelled by the wall for cooling a downstream portion of the cooling surface; and a further wall (133, 151) protruding from the cooling surface and extending at least partially in the streaming direction (101). The platform segment is further configured that a circumferential distance between the wall and the further wall decreases along the streaming direction (101).

Description

technical field [0001] The present invention relates to a platform segment for supporting nozzle guide vanes of a gas turbine and to a nozzle guide vane arrangement for a gas turbine, wherein a cooling surface is provided at the platform segment for cooling at least a part of the platform segment. Furthermore, the invention relates to a method of cooling a nozzle guide vane platform segment by using a cooling fluid directed to cool at least a portion of the nozzle guide vane platform segment. Background technique [0002] The nozzle guide vane is the stationary segment of the gas turbine that directs the exhaust gases from the combustor to the rotor blades located downstream of the nozzle guide vane. The nozzle guide vanes may be supported by a radially inner platform and a radially outer platform. During gas turbine operation, the nozzle guide vanes and the platforms supporting the nozzle guide vanes are subjected to high temperatures from the impingement gases discharged ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04
CPCF05D2260/2212F05D2240/127F01D9/041F01D9/023F05D2240/81F05B2260/201F05B2240/801F05D2260/201F05B2240/122F05B2260/222
Inventor D.布特勒A.戴维斯C.普勒P.M.瓦尔克
Owner SIEMENS AG
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