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Systems and apparatus relating to combustor cooling and operation in gas turbine engines

A technology of gas turbines and burners, which is applied in the direction of gas fuel burners, burners, and combustion chambers, and can solve problems such as complex structures of Venturi tubes and/or combustion chambers

Inactive Publication Date: 2012-07-11
GENERAL ELECTRIC CO
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this configuration can complicate the construction of the venturi and / or combustion chamber and only provide surface cooling of the components of the combustor

Method used

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  • Systems and apparatus relating to combustor cooling and operation in gas turbine engines
  • Systems and apparatus relating to combustor cooling and operation in gas turbine engines
  • Systems and apparatus relating to combustor cooling and operation in gas turbine engines

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Embodiment Construction

[0073] As an initial matter, in order to clearly express the invention of the present application, it may be necessary to select terms referring to and describing certain components or mechanical components of a gas turbine engine. Wherever possible, common industry terminology is used and in a manner consistent with its accepted meaning. However, it is meant that any such terms are to be given a broader meaning and should not be construed narrowly as to unreasonably limit the intended meaning herein and the scope of the appended claims. Those of ordinary skill in the art will recognize that often a particular component may be referred to using several different terms. Additionally, an article described herein as a single component may comprise and, in another context, be composed of multiple component parts, or an article described herein as comprising multiple component parts may be fashioned is, and in some cases refers to, a single part. Therefore, in understanding the s...

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PUM

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Abstract

The invention relates to systems and apparatus relating to combustor cooling and operation in gas turbine engines. Specifically, a venturi (210) inside a combustion chamber (200) of a gas turbine engine is disclosed. The venturi (210) comprises two non-integrated forming components: a fore-piece (302) and a rear-piece (304). The fore-piece (302) comprises a front axis extending portion (306), a converging wall section (308) and a diverging outside wall section (310). The rear-piece (304) comprises a rear axis extending portion (312) and a diverging inside wall section (314). The fore-piece (302) and the rear-piece (304) can be configured to make the diverging inside wall section (314) and the diverging outside wall section (310) close and interval, so that circumferentially extending cooling slots (316) among them are formed.

Description

technical field [0001] The present application generally relates to systems and / or devices for improving the efficiency and / or operation of turbine engines and / or industrial machinery, as used herein and unless specifically stated otherwise, turbine engines and / or Industrial machinery is meant to include all types of gas turbine or rotary engines, including gas turbine engines, aircraft engines, and the like. More particularly, but not in any limiting sense, the present application relates to methods, systems and / or apparatus relating to combustor cooling and operation in gas turbine engines. Background technique [0002] During operation of a gas turbine engine, combustion of a fuel and compressed air mixture occurs within a combustor. To prevent damage to the turbine or other components of the gas turbine engine, the combustion process is stabilized so that the process is contained within the combustor. Usually, a venturi tube is provided in the combustion chamber of the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23D14/46
CPCY02T50/675F23R2900/03042F23R3/16F23R3/06F23R3/005Y02T50/60
Inventor K·V·斯里哈A·P·德赛
Owner GENERAL ELECTRIC CO
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