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Combustion liner having turbulators

A turbulator, turbulent flow technology, applied in the combustion chamber, combustion method, combustion equipment and other directions, can solve the problem of shortening the life of the liner

Inactive Publication Date: 2012-12-12
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These mechanisms shorten bushing life, requiring early component replacement

Method used

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  • Combustion liner having turbulators
  • Combustion liner having turbulators
  • Combustion liner having turbulators

Examples

Experimental program
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Embodiment Construction

[0058] see figure 1 with figure 2 , a typical gas turbine includes a transition piece 10 through which hot combustion gases pass from an upstream combustor (as represented by a combustion liner 12 ) to a first stage of the turbine, indicated at 14 . Flow from the gas turbine compressor exits the axial diffuser 16 and enters into the compressor discharge casing 18 . Approximately 50% of the compressor discharge air passes through the orifices 20 formed along and around the transition piece impingement sleeve 22 to flow between the transition piece 10 and the radially outer transition piece impingement sleeve 22 within the annular region or annulus 24 (or second flow annulus). The remaining approximately 50% of the compressor discharge flow passes into the flow sleeve bore 34 of the upstream combustion liner cooling sleeve (not shown) and into the annulus between the cooling sleeve and the liner and ultimately in the annulus 24 mixed with air. This combined air is ultimatel...

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Abstract

The invention relates to a combustion liner having turbulators. A combustor for a turbine is provided. The combustor includes a plurality of fuel nozzles (310) and a combustion zone is aligned with a combustion process associated with each of the fuel nozzles. A combustion liner (400) includes a plurality of turbulator groups (430, 440), and each of the turbulator groups has or more individual turbulators. Each of the turbulator groups (430, 440) is aligned with a hot streak (420) caused by the combustion zone associated with the fuel nozzle. Each of the turbulator groups are circumferentially spaced from a neighboring turbulator group.

Description

technical field [0001] The present invention relates to internal cooling in gas turbines; and in particular to an apparatus for providing better and more uniform cooling in the combustion liner of the turbine. Background technique [0002] Conventional gas turbine combustors use diffusion (ie, non-premixed) combustion, where fuel and air enter the combustion chamber individually. The mixing and incineration process produces flame temperatures in excess of 3900°F. Since conventional combustors and / or transition pieces with liners can typically withstand a maximum temperature of only about 1500°F for about ten thousand hours (10,000 hours), measures must be taken to protect the combustors and / or transition pieces. This is typically done by film cooling, which involves introducing relatively cooler compressor air into a plenum formed by the combustor liner around the outside of the combustor. In this prior arrangement, air from the plenum passes through air holes in the combu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/16F23R3/26
CPCF23R3/04F23R3/002F23R2900/03045
Inventor P.B.梅尔顿D.W.奇拉D.K.托伦托
Owner GENERAL ELECTRIC CO