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Interlocking stage for airfoils

A technology of locking interface and shield, applied in the direction of engine elements, blade support elements, machines/engines, etc., can solve problems such as expensive and time-consuming

Inactive Publication Date: 2019-11-15
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This can be a time consuming and expensive exercise

Method used

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  • Interlocking stage for airfoils
  • Interlocking stage for airfoils
  • Interlocking stage for airfoils

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Embodiment Construction

[0040] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar symbols have been used in the drawings and the specification to designate the same or similar parts of the present invention.

[0041] As used herein, the terms "first", "second" and "third" may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of the various components.

[0042] The terms "forward" and "rearward" refer to relative positions within the gas turbine engine or vehicle, and to the normal operating attitude of the gas turbine engine or vehicle. For example, with respect to a gas turbine engine, forward refers to a location closer to the engine inlet, and aft refers to a location closer to the engine nozzle or exhaust. ...

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Abstract

An interlocking stage for airfoils is provided. A method is provided for repairing a turbine engine including a stage of vanes, the stage of vanes including a first vane having a first shroud and a second vane having a second shroud. The method includes: inspecting the stage of vanes in situ, wherein inspecting the stage of vanes in situ includes determining an actual gap width of a gap defined between the first shroud of the first vane and the second shroud of the second vane is greater than a predetermined threshold; and installing a shim in situ in the gap between the first shroud and the second shroud.

Description

technical field [0001] The subject matter generally relates to interlocking airfoil stages, and methods of repairing the same. Background technique [0002] In some gas turbine engines, the serial flow arrangement includes: a compressor section, which includes a low pressure compressor and a high pressure compressor for compressing air flowing through the engine; a combustor, which combines fuel with compressed air mixing so that the mixture can be ignited; and a turbine section comprising a high pressure turbine and a low pressure turbine for powering the compressor section. [0003] Each of the compressor and turbine may include multiple stages of buckets for adding energy to or extracting energy from the air flowing therethrough. One or more stages of buckets may have buckets configured to interlock at their respective radially outer ends to reduce relative movement therebetween. For example, a low pressure turbine may include a stage of low pressure turbine rotor blade...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/22
CPCF01D5/005F01D5/22F05D2240/70F01D5/225F05D2230/23F05D2230/80F05D2230/90F05D2230/30Y02T50/60F01D5/282F01D5/284F05D2300/6033B23P6/005F01D9/041F05D2220/3215F05D2240/12F05D2260/80
Inventor 大卫·斯科特·迪温斯基
Owner GENERAL ELECTRIC CO