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Gas turbines having flexible chordal hinge seals

A technology for turbines and seals, applied in the field of flexible chordwise hinge seals, which can solve problems such as increasing the complexity and cost of gas turbines

Inactive Publication Date: 2013-07-24
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the use of such secondary seals adds significantly to the complexity and cost of manufacturing the gas turbine

Method used

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  • Gas turbines having flexible chordal hinge seals
  • Gas turbines having flexible chordal hinge seals
  • Gas turbines having flexible chordal hinge seals

Examples

Experimental program
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Embodiment Construction

[0066] see figure 1, shows a representative embodiment of a portion of gas turbine 10 . The turbine 10 receives combustion hot gases from an annular array of combustors (not shown), which deliver the hot gases through an adapter 12 for fluid flow along an annular hot gas path 14 . Turbine stages are arranged along the hot gas flow path 14 . Each stage includes a plurality of circumferentially spaced buckets mounted on and forming part of a turbine rotor and a circumferentially spaced plurality of stator blades. An annular array of nozzles is formed. For example, the first stage includes a plurality of circumferentially spaced stator blades 20 and a plurality of circumferentially spaced buckets 16 mounted on the first stage rotor wheel 18 . Likewise, the second stage includes a plurality of circumferentially spaced apart stator blades 26 and a plurality of buckets 22 mounted on a second stage rotor wheel 24 . Additionally, the third stage includes a plurality of circumferen...

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PUM

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Abstract

Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring.

Description

technical field [0001] The present invention relates generally to gas turbines and, more particularly, to flexible chordal hinge seals for sealing turbine nozzles within gas turbines. Background technique [0002] In a gas turbine, the hot gases of combustion flow from the combustor through nozzles and buckets of the first stage and nozzles and buckets of subsequent turbine stages. The first stage nozzle comprises cast nozzle segments in an annular array or annular assembly, each segment comprising one or more nozzle stator vanes. Each first stage nozzle segment also includes an inner band portion and an outer band portion radially spaced from each other. When the nozzle segments are assembled, the stator vanes are circumferentially spaced from one another to form an annular array between an annular inner band and an annular outer band. An outer shroud or retaining ring attached to the outer band of the first stage nozzle supports the first stage nozzle within the gas flow...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/02
CPCF05D2240/57F01D11/005
Inventor D·D·斯努克E·D·本杰明D·J·哈曼楚克
Owner GENERAL ELECTRIC CO