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Combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine

A technology of burners and turbines, which is applied in the direction of combustion methods, burners, gas fuel burners, etc., and can solve problems such as low-efficiency operation of gas turbine engines

Inactive Publication Date: 2009-10-21
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At this point, if the gas turbine engine is still found to be operating inefficiently, it may be necessary to repeat the process

Method used

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  • Combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine
  • Combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine
  • Combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine

Examples

Experimental program
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Embodiment Construction

[0012] refer to figure 1 An exemplary gas turbine engine 1 includes a compressor (not shown), a combustor 10 and a turbine (not shown) located downstream of the combustor 10 . Compressor 10 includes a combustor 20 in which combustion of air and fuel occurs, a transition duct 25 extending downstream from combustor 20 , and a casing 40 enclosing combustor 10 .

[0013] Combustion chamber 20 includes an annular combustion liner 21 . A venturi throat region 22 is defined along the combustion liner 21 and includes a converging portion at which the combustion liner 21 narrows and a diverging portion disposed downstream of the converging portion and at which the combustion liner 21 expands. Exhaust ports 23 are defined along combustion liner 21 to allow cooling and to assist combustion proceeding into combustion chamber 20 . The blending port 24 is defined in the combustion liner 21 at a second axial location 82 of the combustion chamber 20 . The blend port 24 allows blend air to ...

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PUM

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Abstract

The present invention relates to a combustor of a turbine, a method of retro-fitting the combustor of a turbine and a method of building the combustor of a turbine. Specifically, a combustor of a turbine, a method of retro-fitting a combustor of a turbine and a method of building a combustor of a turbine are each provided. The combustor includes a combustion chamber along which a dilution breach is defined, a casing perimetrically surrounding the combustion chamber so as to define an airflow between the casing and the combustion chamber, the airflow being configured to supply dilution air to the combustion chamber via the dilution breach, and an easy to adjust dilution airflow tuning part disposed on the casing and in communication with the airflow. The dilution airflow tuning part is configured to increase and / or decrease an available amount of the dilution air to be supplied to the combustion chamber.

Description

technical field [0001] Aspects of the invention relate to a combustor of a turbomachine, a method of retrofitting a combustor of a turbomachine, and a method of constructing a combustor of a turbomachine, and, more particularly, to a combustor of a turbomachine including admixed air conditioning components, retrofitting a combustor with A method of combustor for a turbine incorporating air conditioning components, and a method of constructing a combustor for a turbine incorporating air conditioning components. Background technique [0002] Inefficiencies have been noted in the installation and / or repair of gas turbine engines as regulatory requirements change. In other words, it should be understood that maintaining a certain amount of entrained air within the combustion chamber of a gas turbine engine is necessary for efficient operation and regulation of the gas turbine engine. It should also be appreciated that maintaining such amounts of admixed air can be achieved by i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23D14/02F23D14/62
CPCF23R3/26F23R3/06F23R2900/00016Y10T29/49346
Inventor W·赫斯勒P·波波维克
Owner GENERAL ELECTRIC CO