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Cooling a one-piece can combustor and related method

A combustor and combined combustor technology, applied in the field of turbine components

Inactive Publication Date: 2011-01-05
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, forced convection alone cannot effectively cool a one-piece pipe

Method used

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  • Cooling a one-piece can combustor and related method
  • Cooling a one-piece can combustor and related method
  • Cooling a one-piece can combustor and related method

Examples

Experimental program
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Effect test

Embodiment Construction

[0012] refer to figure 1 , an exemplary but non-limiting embodiment of the present invention includes a cylindrical one-piece combination combustor liner / transition piece (or one-piece duct) 10 of compound shape extending directly from a circular combustor head end 12 To a generally rectangular but arcuate section 14 connected to the first stage of a turbine 16 . The one-piece duct 10 may be formed from two halves or several pieces that are welded or joined together for ease of assembly or manufacture. Likewise, a one-piece flow sleeve 18 transitions directly from the circular combustor head end 12 to the aft frame 20 . The one-piece flow sleeve 18 may also be formed from two halves and welded or joined together for ease of assembly. The connection point between the flow sleeve 18 and the rear frame 20 forms a substantially closed end to the cooling annular space 22 located radially between the flow sleeve 18 and the one-piece pipe 10 .

[0013] Additional gas turbine combu...

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PUM

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Abstract

The invention relates to a cooling a one-piece can combustor and related method. A cooling arrangement for cooling a single-piece, combined combustor liner / transition piece (10) substantially enclosed within a surrounding flow sleeve, with a cooling annulus (22) radially between the flow sleeve and the single-piece combined combustor liner / transition piece, the cooling arrangement including a first plurality of impingement cooling holes (40) in the flow sleeve, the plurality of impingement cooling holes having first diameters and arranged to direct cooling air onto designated areas of the single-piece, combined combustor liner / transition piece; and a second plurality of effusion cooling holes (36) in the single-piece, combined combustor liner / transition piece having second diameters smaller than the first diameters, and located to cool by effusion other areas of the single-piece, combined combustor liner / transition piece.

Description

technical field [0001] The present invention relates generally to turbine components, and more particularly to cooling gas turbine combustors. Background technique [0002] Industrial gas turbine combustors are typically designed to include a plurality of discrete combustion chambers or "cans" arranged in an array around the circumference of the turbine rotor. Conventionally, the walls of an industrial gas turbine can combustor are formed from two main components: a cylindrical or conical sheet metal liner that joins the dome end of the combustor; A sheet metal transition piece of circular cross-section to an arcuate sector of the inlet to the first stage of the turbine. The two combustor components are connected together in end-to-end relationship by means of a flexible connection, which requires the consumption of a portion of the compressor discharge air in the cooling flow and leakage at the connection. [0003] In commonly owned U.S. Patent No. 7,082,766, a can combus...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23D14/78
CPCF23R2900/03044F23R3/04F23R2900/03041
Inventor R·J·基拉K·W·麦马汉
Owner GENERAL ELECTRIC CO