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Stator vane system usable within a gas turbine engine

A gas turbine and engine technology, applied in the field of support system of the stator vane airfoil, to achieve the effect of increasing ease, easy assembly and replacement, and reducing lifting time

Inactive Publication Date: 2017-03-22
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This problem has been addressed in US Patent 8,123,354 B2, but it requires at least thirteen custom parts and at least twenty-two steps to assemble the stator

Method used

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  • Stator vane system usable within a gas turbine engine
  • Stator vane system usable within a gas turbine engine
  • Stator vane system usable within a gas turbine engine

Examples

Experimental program
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Embodiment Construction

[0028] as in Figure 1-6 As shown in , a stator assembly 10 that may be used in a gas turbine engine 12 is disclosed and is configured to constrain the inner and outer end walls 14, 16 to limit deflection and prevent rotor disk 18 clearance loss. The stator assembly 10 may be formed from a plurality of stator vanes 20 having inner and outer end walls 14 , 16 coupled together by a first radially outer tie bar. In at least one embodiment, as in image 3 As shown in , the first and second radially outer connecting bars 22, 24 may form first and second stator vane segments 26, 28 which together form a circumferentially extending The stator assembly 10. The inner and outer end walls 14, 16 may be coupled together with one or more circumferentially extending alignment pins 30 that limit deflection. The stator assembly 10 may include one or more deformable seals 32 extending radially inwardly from the inner end wall 14 .

[0029] In at least one embodiment, a stator assembly 10 ...

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PUM

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Abstract

A stator assembly (10) for a gas turbine engine (12), comprising: a plurality of stator vanes (20), each formed from a generally elongated airfoil (34) having a leading edge (36), a trailing edge (38), a pressure side (40), a suction side (42), an inner endwall (14) coupled to a first end (44) and an outer endwall (16) coupled to a second end (46) opposite the first end (44); a first radially outer tie bar (22) coupled to each outer endwall (16) of a portion of the stator vanes (20); at least one inner alignment pin (48) extending between adjacent inner endwalls (14) to couple adjacent inner endwalls (14) together; at least one forward inner seal ring (50) attached to the inner endwall (14); and at least one deformable seal (52) coupled to at least one radially inner surface (54) of the forward inner seal ring (50), wherein the at least one deformable seal (52) includes an upstream facing contact surface (110) and radially inward facing contact surface (112).

Description

technical field [0001] The present invention is directed generally to stator vane airfoils within gas turbine engines, and more particularly to support systems for stator vane airfoils. Background technique [0002] Turbine engines typically include rows of stationary compressor stator vanes extending radially inward from a casing, and include rows of rotatable compressor blades attached to a rotor assembly for turning the rotor. A conventional turbine engine typically includes a segment with a plurality of stationary airfoils, collectively referred to as a stator. The stator segments deflect in the upstream direction under a steady gas pressure load, and this deflection varies around the circumference depending on how the segments are constrained to the casing. The unconstrained ends of the segments deflect more and have less axial clearance to the upstream rotor disk. This problem has been addressed in US Patent 8,123,354 B2, but it requires at least thirteen custom part...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F01D25/24F01D11/00F01D11/12
CPCF01D9/042F01D11/001F01D11/127F01D25/246F05D2230/64F05D2260/30F05D2300/505F04D29/083F04D29/542F04D29/644
Inventor E.格里芬
Owner SIEMENS AG