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Rear end liner assembly with turbulator and its cooling method

A lining, back-end technology for internal cooling applications

Inactive Publication Date: 2009-08-26
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In Dry Low NOx (DLN) emissions systems, this cooling can only be provided as cold convection

Method used

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  • Rear end liner assembly with turbulator and its cooling method
  • Rear end liner assembly with turbulator and its cooling method
  • Rear end liner assembly with turbulator and its cooling method

Examples

Experimental program
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Embodiment Construction

[0018] figure 1 The rear end of the burner is schematically depicted in cross-section. As can be seen, in this example the transition piece 12 includes a radially inner transition piece body 14 and a radially outer transition piece impingement sleeve 16 spaced from the transition piece body 14 . Upstream of the transition piece 12 is a combustion liner 18 and a combustor flow sleeve 20 defined in surrounding relationship therewith. The circled area is the forward sleeve assembly 22 of the transition piece.

[0019] Airflow from a gas turbine compressor (not shown) enters casing 24 . In an exemplary embodiment, approximately 50% of the compressor discharge air passes through openings (not shown in detail) formed along and around the transition piece impingement sleeve 16 to flow into the transition piece body 14 and The radially outer transition piece impinges on the annular region or ring 26 between the bushings 16 . The remainder of the compressor discharge gas flow (appr...

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Abstract

The engine has a sheet cover (140) arranged between a rear lining end (150) of a combustion chamber lining and a Hula seal (38). An air flow channel is defined between the cover and the rear lining end. An outer surface of the rear lining end radially defines the channel. The outer surface includes multiple transverse turbulators (142) that are spaced at a distance from the cover and projected to the cover, and includes multiple supports (144) that are engaged in the cover and extended to the cover, in order to arrange the cover at a distance from the turbulators for definition of the channel. An independent claim is also included for a method for cooling a transition area between a combustion section and an outlet section of a turbine.

Description

technical field [0001] The present invention relates to internal cooling in gas turbine engines and, more particularly, to assemblies and methods for providing better and more uniform cooling in the transition region between the combustion and exhaust sections of the turbine. Background technique [0002] Conventional gas turbine combustors use diffusion (ie, non-premixed) combustion, where fuel and air enter the combustion chamber separately. The process of mixing and burning produces very high flame temperatures. Because conventional lined combustors and / or transition pieces cannot withstand such high temperatures, steps must be taken to protect the combustor and / or transition piece. This is typically accomplished by film cooling, which involves directing relatively cool compressor air into a plenum formed by a combustor liner surrounding the combustor exterior. In this prior configuration, air from the plenum passes through bleed holes in the combustor liner and then pa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/18F23R3/04F02C7/20
CPCF23R3/04F05B2260/2241F01D9/023F05D2260/22141F05D2260/2214F05B2260/224F23R2900/03045
Inventor T·E·约翰逊P·梅尔顿
Owner GENERAL ELECTRIC CO