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Platform cooling of a turbine blade assembly

a technology of turbine blades and cooling media, which is applied in the field of platform cooling, can solve the problems components failing, and achieve the effect of reducing the cooling effect of the cooling medium

Inactive Publication Date: 2014-04-10
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention has certain benefits and advantages that are described below. These benefits may be easily understood by reading the description or by practicing the invention.

Problems solved by technology

During operation, various components within the gas turbine are subjected to high temperature flows, which can cause the components to fail.
However, as the cooling medium flows from the pressure side, heat energy is transferred to the cooling medium, thereby reducing the cooling effect of the cooling medium as it flows through and / or across the platform.

Method used

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  • Platform cooling of a turbine blade assembly
  • Platform cooling of a turbine blade assembly
  • Platform cooling of a turbine blade assembly

Examples

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Embodiment Construction

[0020]Reference will now be made in detail to 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. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. In addition, the terms “upstream” and “downstream” refer to the relative location of components in a fluid pathway. For example, component A is upstream from component B if a fluid flows from component A to component B. Conversely, component B is downstream from component A if component B receives a fluid flow from component A.

[0021]Each example is provided by way of explanation of the invent...

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PUM

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Abstract

A turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side.

Description

FIELD OF THE INVENTION[0001]The present invention generally involves cooling a platform of a turbine blade. More specifically, the invention involves a platform cooling circuit that defines a fluid flow path from a suction side of the platform to a pressure side of the platform.BACKGROUND OF THE INVENTION[0002]Turbines are widely used in fields such as power generation. A conventional gas turbine may generally include a compressor, a combustor, and a turbine. During operation, various components within the gas turbine are subjected to high temperature flows, which can cause the components to fail. Since higher temperature flows generally result in increased performance, efficiency, and power output of the gas turbine, the components that are subjected to high temperature flows must be cooled to allow the gas turbine to operate at increased temperatures.[0003]Various strategies are known in the art for cooling various gas turbine components. For example, a cooling medium may be route...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/08
CPCF01D5/081F01D5/187F05D2240/81F05D2260/205
Inventor BOYER, BRADLEY TAYLORGOOD, RANDALL RICHARD
Owner GENERAL ELECTRIC CO