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Turbine airfoil trailing edge cooling hole plug and slot

A technology of turbine airfoils and cooling holes, applied in the direction of engine components, blade support components, climate sustainability, etc., can solve the problem of reducing the overall efficiency of the engine

Inactive Publication Date: 2015-01-14
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Cooling air is typically compressor exhaust, which diverts from the combustion process and thus reduces the overall efficiency of the engine

Method used

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  • Turbine airfoil trailing edge cooling hole plug and slot
  • Turbine airfoil trailing edge cooling hole plug and slot
  • Turbine airfoil trailing edge cooling hole plug and slot

Examples

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Embodiment Construction

[0027] figure 1 Illustrated in is an exemplary gas turbine engine high pressure turbine stage 10 about an engine centerline axis 8 and positioned between a combustor 20 and a low pressure turbine (LPT) 24 . The combustor 20 mixes fuel with pressurized air for generating hot combustion gases 19 which flow downstream D through the turbine.

[0028] The high pressure turbine stage 10 includes a turbine nozzle 28 upstream of a high pressure turbine (HPT) 22 through which hot combustion gases 19 are discharged from the combustor 20 . The exemplary embodiment of the high pressure turbine 22 shown herein includes at least one row of circumferentially spaced high pressure turbine blades 32 . Each of the turbine blades 32 includes a turbine airfoil 12 integrally formed with the platform 14 and an axial entry dovetail 16 for mounting the turbine blade on the periphery of the supporting rotor disk 17 .

[0029] refer to figure 2 , the airfoil 12 extends radially outward along a span...

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Abstract

A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes disposed in pressure sidewall. All or a plurality of cooling holes end at a trailing edge cooling slot extending chordally substantially to an airfoil trailing edge. Each cooling hole includes a curved inlet, a metering section with a constant area and constant width flow cross section, and a spanwise diverging section leading into slot. Axial partitions extend chordally between and radially separate cooling holes along span. Aft ends of partitions include swept boat tails. Upper and lower deck sidewalls spanwise bound a deck of slot and extend outward to an external surface of pressure sidewall. Fillets between sidewalls and deck have fillet radii substantially the same size as bottom corner radii of flow cross section of diverging sections adjacent bottom corner radii.

Description

[0001] Cross References to Related Applications [0002] This application claims U.S. Provisional Patent Application No. 61 / 644,618, entitled "Turbine airfoil trailing edge cooling hole plug and slot," filed May 9, 2012, The disclosure of this application is incorporated herein by reference. technical field [0003] The present invention relates generally to gas turbine engine airfoil cooling, and more particularly, to turbine airfoil trailing edge cooling holes leading to trailing edge cooling slots. Background technique [0004] In a gas turbine engine, air is pressurized in a compressor and mixed with fuel in a combustor to produce hot combustion gases. This hot gas is directed through stages of the turbine, which extract energy from the hot gas to drive a compressor and perform work, such as driving an upstream fan in typical aerospace turbofan engine applications. [0005] The turbine stage includes a stationary turbine nozzle having rows of hollow vanes that direct ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/186F01D5/187Y02T50/676Y02T50/673F01D5/189F01D5/188Y02T50/60
Inventor R.F.小伯格霍尔斯D.L.杜尔斯托克
Owner GENERAL ELECTRIC CO
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