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Encapsulated cooling for turbine shrouds

A shroud and turbine technology, applied in the cooling of turbine/propulsion device, engine cooling, gas turbine device, etc., can solve the problems of increasing the complexity, assembly time and cost of gas turbine engines

Active Publication Date: 2017-09-05
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, splined seals add complexity, assembly time and cost to gas turbine engines

Method used

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  • Encapsulated cooling for turbine shrouds
  • Encapsulated cooling for turbine shrouds
  • Encapsulated cooling for turbine shrouds

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Embodiment Construction

[0056] Reference will now be made in detail to the present 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 designations in the drawings and description are used to refer to the same or similar parts of the present invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish components from one another, and are not intended to indicate the location or importance of individual components. The terms "upstream" and "downstream" refer to relative flow directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction of flow from which fluid flows, and "downstream" refers to the direction of flow to which fluid flows.

[0057] Each example is provided by way of explanation of the invention, not limitation of the inv...

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PUM

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Abstract

The invention relates to encapsulated cooling for turbine shrouds. A shroud (100) for a gas turbine (10,14) is provided. The shroud (100) can include an outer box (102) having a first wall (186) and a second wall (180) circumferentially spaced apart from the first wall (186). An inner box (110) is positioned within the outer box (102). The inner box (110) defines one or more passageways (136) extending therethrough and a first chamber (112). The inner box (110) and the outer box (102) collectively define a second chamber (114). The one or more passageways (136) defined by the inner box (110) fluidly couple the first chamber (112) and the second chamber (114). The first wall (186) of the outer box (102) defines a first boss (198) and first notch (210), and the second wall (180) of the outer box (102) defines a second boss (196) and notch (212). Further, provided is a gas turbine containing multiple such shrouds (100).

Description

technical field [0001] The present disclosure relates generally to gas turbine engines, and more particularly, to shrouds for gas turbine engines. Background technique [0002] A gas turbine engine generally includes, in serial order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air enters the inlet of the compressor section, where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with compressed air and combusted in the combustion zone, creating gases. Gases flow from the combustion section through a hot gas path defined within the turbine section and then exit the turbine section via the exhaust section. [0003] In a particular configuration, the turbine section includes a high pressure turbine ("HP turbine") and a low pressure turbine ("LP turbine") sequentially in series. HP turbines and LP turbines include one or more axially spaced rows of circu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D25/12F01D25/14
CPCF01D25/12F01D25/14F01D11/005F01D11/24F01D25/246F05D2240/11F05D2230/644F05D2250/281F01D11/08F02C3/04F02C7/18F02C7/28F05D2220/32F05D2260/20
Inventor M.W.马鲁斯科D.L.杜尔斯托克
Owner GENERAL ELECTRIC CO