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System and method for flow control in gas turbine engine

A gas turbine and air flow technology, applied in the field of flow control, can solve the problems of reducing the performance of gas turbine engines

Inactive Publication Date: 2012-11-28
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Unfortunately, flow turbulence can be created as the compressed air flows through the annular gap, reducing the performance of the gas turbine engine

Method used

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  • System and method for flow control in gas turbine engine
  • System and method for flow control in gas turbine engine
  • System and method for flow control in gas turbine engine

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Embodiment Construction

[0099] One or more specific embodiments of the present invention will be described below. In an effort to provide a concise description of these embodiments, not all features of an actual implementation may be described in the specification. It should be understood that when developing any such actual implementation, such as in any engineering or design project, a number of implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related and business-related constraints , the developer's specific goals can vary from implementation to implementation. Moreover, it should be understood that such a development effort might be complex and time consuming, but would nonetheless be a routine undertaking of design, production, and manufacture for those of ordinary skill having the benefit of this disclosure.

[0100] When introducing elements of various embodiments of the invention, the articles "a," "an," "the," and "sai...

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Abstract

The invention relate to a system and a method for flow control in a gas turbine engine. The system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and an airflow guide vane disposed in the air passage. The airflow guide vane includes an upstream vane portion and a downstream vane portion. The upstream vane portion is oriented at an angle from an axial axis of the gas turbine combustor. The downstream vane portion is aligned with the axial axis. The airflow guide vane is configured to remove a circumferential swirl of an airflow upstream of the airflow guide vane to straighten the airflow downstream of the airflow guide vane along the axial axis.

Description

technical field [0001] The subject matter disclosed herein relates to combustors and, more specifically, to flow control within gas turbine engines. Background technique [0002] Various combustion systems include a combustion chamber in which fuel and air are combusted to produce hot gases. For example, a gas turbine engine may include one or more combustors configured to receive compressed air from a compressor, inject fuel into the compressed air, and generate hot combustion gases to drive the turbine engine. Each combustor may include one or more fuel nozzles, a combustion zone within the combustion liner, a flow sleeve surrounding the combustion liner, and a gas transition duct. Compressed air from the compressor flows through the gap between the combustion liner and the flow sleeve to the combustion zone. The compressed air flow may include rotating or circumferential vortex components. Unfortunately, flow turbulence can be created as the compressed air flows throug...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F23R3/16F23R3/26
CPCY02T50/675F23R3/48F23R2900/03043F23R3/002Y02T50/60
Inventor P.B.梅尔顿D.W.奇拉R.J.罗尔森A.R.罕
Owner GENERAL ELECTRIC CO