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System for cooling turbine engine

A technology for cooling turbines, turbines, applied to engine components, engine functions, machines/engines, etc.

Active Publication Date: 2016-10-12
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, undesirably high thermal stresses in various turbine hardware components can occur due to thermal gradients associated with hot combustion gas temperatures and significantly lower cooling medium temperatures

Method used

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  • System for cooling turbine engine
  • System for cooling turbine engine
  • System for cooling turbine engine

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Embodiment Construction

[0137] 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 designate features in the drawings. Like or analogous symbols in the drawings and description are used to refer to like or analogous parts of the present invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one element from another, and are not intended to denote the position or importance of individual elements. . The terms "upstream" and "downstream" refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction from which a fluid flows, and "downstream" refers to the direction to which a fluid flows.

[0138] Referring now to the drawings, wherein like numerals indicate like elements throughout, figure 1 is a schematic cross-sectional vi...

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Abstract

In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.

Description

technical field [0001] The subject matter generally relates to turbine engines. More specifically, the subject matter relates to systems for cooling various turbine components of turbine engines, such as turbine shroud assemblies. Background technique [0002] A gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section, in sequential order. In operation, air enters the inlet of the compressor section where one or more axial compressors gradually compress the air until it reaches the combustion section. Fuel is mixed with compressed air and combusted in the combustion section to provide combustion gases. Combustion gases are sent from the combustion section to the turbine section. In certain configurations, the turbine section includes a high pressure (HP) turbine and a low pressure (LP) turbine in a sequential flow-through sequence. The HP turbine and the LP turbine at least partially define the hot gas pa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D5/18F01D25/12
CPCF01D5/18F01D9/02F01D25/12F01D9/065F01D11/24F05D2260/205Y02T50/60F01D5/187F01D9/041F01D11/08F05D2220/30F05D2220/32F05D2240/11F05D2240/12F05D2240/30F05D2260/201F05D2260/202
Inventor 宁卫D.P.德伊M.V.斯林瓦斯
Owner GENERAL ELECTRIC CO
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