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Gas turbine airfoil with cooling enhancement

a technology of airfoil and turbine engine, which is applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of high stress on rotating buckets (or airfoils) and stationary stator vanes

Inactive Publication Date: 2015-04-09
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The present patent aims to enhance the cooling of turbine nozzle vanes or blades in order to improve the efficiency and operation of turbine engines.

Problems solved by technology

During operation, because of the extreme temperatures in the hot-gas path, the velocity of the working fluid, and the rotational velocity of the engine, the rotating buckets (or airfoils) and the stationary stator vanes become highly stressed due to extreme mechanical and thermal loads.

Method used

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  • Gas turbine airfoil with cooling enhancement
  • Gas turbine airfoil with cooling enhancement
  • Gas turbine airfoil with cooling enhancement

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Embodiment Construction

[0020]FIG. 1 illustrates in schematic form a gas turbine system 10 that, as described further herein, includes stationary vanes and rotating blades or buckets that may be provided with internal cooling circuits. In this otherwise conventional arrangement, air supplied via inlet 12 is pressurized in a compressor 14 and mixed with fuel in one or more combustors 16 where it is ignited to thereby generate hot combustion gases. Energy is extracted from the combustion gases in one or more turbine stages 18 disposed downstream of the combustors, to drive a generator 20 producing electric power. The extracted energy may also be used to drive the compressor 14, and note that the turbine rotor 22 may be common to the compressor, turbine stages and generator. The invention described herein, however, is not limited to just the illustrated gas turbine system. Further in that regard, the cooling circuits described herein are fully compatible with various film-cooling configurations utilizing air ...

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PUM

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Abstract

A turbine nozzle vane segment includes one or more nozzle vanes extending between radially inner and outer side walls, each nozzle vane having a peripheral edge wall extending between a leading edge and a trailing edge of the vane. In one exemplary embodiment, at least one substantially radially-oriented cooling channel is formed in the peripheral edge wall at the leading edge, with openings at opposite ends of the cooling channel. The location and length of the cooling channels may vary about the peripheral edge wall, and the inner cavity of the vane may be provided with ribs extending along and adjacent the one or more cooling channels to reinforce the wall and to also provide additional cooling surface areas in the inner cavity.

Description

BACKGROUND OF THE INVENTION[0001]This present application relates generally to improving the efficiency and / or operation of turbine engines. More specifically, but not by way of limitation, the present application relates to enhancing the cooling of turbine nozzle vanes or blades.[0002]A gas turbine engine typically includes a compressor, one or more combustors, and at least one turbine section. The compressor and turbine section generally include rows of vanes and buckets that are axially stacked in stages. Each stage may include alternating rows of circumferentially-spaced stator vanes, which are stationary, and circumferentially-spaced buckets, that are mounted on a wheel fixed to the turbine rotor. In operation, the rotor blades in the compressor rotate with the rotor to compress a flow of air supplied to the compressor. Most of the compressed air is mixed with gaseous or liquid fuel in the one or more combustors and ignited to provide a stream of hot gases, which is expanded th...

Claims

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Application Information

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IPC IPC(8): F01D5/18F01D9/02
CPCF01D9/02F01D5/187F01D9/065Y02T50/60
Inventor SARANGAPANI, SANDEEP MUNSHIPATIL, AJAY GANGADHARRAO, POORNA CHANDRA
Owner GENERAL ELECTRIC CO