Turbine Shroud Cooling Assembly for a Gas Turbine System

Inactive Publication Date: 2013-11-28
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention describes a cooling system for a gas turbine system, specifically the turbine section. The system includes an inner shroud component that is cooled by a cooling flow from a cooling source. The inner shroud component has a base portion that is in direct contact with the hot gas path and a rib that extends from the base portion to the leading edge of the inner shroud component. The rib has a main passage that receives the cooling flow and cools the inner shroud component. This cooling system helps to protect the inner shroud component from high temperatures and improve the durability and performance of the gas turbine system.

Problems solved by technology

High temperatures along the hot gas path can heat turbine components, causing degradation of components.
Such cooling schemes typically result in excessive cooling flow from a cooling source, thereby sacrificing overall efficiency of the gas turbine system.

Method used

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  • Turbine Shroud Cooling Assembly for a Gas Turbine System
  • Turbine Shroud Cooling Assembly for a Gas Turbine System
  • Turbine Shroud Cooling Assembly for a Gas Turbine System

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Embodiment Construction

[0014]Referring to FIG. 1, a gas turbine system is schematically illustrated with reference numeral 10. The gas turbine system 10 includes a compressor 12, a combustor 14, a turbine 16, a shaft 18 and a fuel nozzle 20. It is to be appreciated that one embodiment of the gas turbine system 10 may include a plurality of compressors 12, combustors 14, turbines 16, shafts 18 and fuel nozzles 20. The compressor 12 and the turbine 16 are coupled by the shaft 18. The shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form the shaft 18.

[0015]The combustor 14 uses a combustible liquid and / or gas fuel, such as natural gas or a hydrogen rich synthetic gas, to run the gas turbine system 10. For example, fuel nozzles 20 are in fluid communication with an air supply and a fuel supply 22. The fuel nozzles 20 create an air-fuel mixture, and discharge the air-fuel mixture into the combustor 14, thereby causing a combustion that creates a hot pressurized exhaust gas. T...

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Abstract

A turbine shroud cooling assembly for a gas turbine system includes an inner shroud component disposed within a turbine section of the gas turbine system and proximate a hot gas path therein, wherein the inner shroud component includes a base portion in direct contact with the hot gas path. Also includes is a rib protruding radially away from the base portion and disposed proximate at least one cavity configured to receive a cooling flow from a cooling source, wherein the cooling flow passes through the main passage of the rib for cooling the inner shroud component.

Description

BACKGROUND OF THE INVENTION[0001]The subject matter disclosed herein relates to gas turbine systems, and more particularly to a turbine shroud cooling assembly for cooling turbine shrouds of such gas turbine systems.[0002]In gas turbine systems, a combustor converts the chemical energy of a fuel or an air-fuel mixture into thermal energy. The thermal energy is conveyed by a fluid, often compressed air from a compressor, to a turbine where the thermal energy is converted to mechanical energy. As part of the conversion process, hot gas is flowed over and through portions of the turbine as a hot gas path. High temperatures along the hot gas path can heat turbine components, causing degradation of components.[0003]A turbine shroud assembly is an example of a component that is subjected to the hot gas path and often comprises two separate pieces, such as an inner shroud and an outer shroud. Based on the immediate proximity of the inner shroud to the hot gas path, various cooling schemes ...

Claims

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Application Information

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IPC IPC(8): F01D25/00
CPCF01D9/04F01D11/24F05D2240/11F05D2260/22141
InventorROGERS, MICHELLE JESSICAFOSTER, GREGORY THOMAS
OwnerGENERAL ELECTRIC CO