System and method for flow control in gas turbine engine

a gas turbine engine and flow control technology, applied in the field of combustion chambers, can solve problems such as the decrement of the performance of the gas turbine engine, and achieve the effect of reducing the swirl of the airflow and discharging the airflow

Inactive Publication Date: 2012-11-29
GENERAL ELECTRIC CO
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0006]In a third embodiment, a method includes straightening an airflow in an air passage between a combustion liner and a flow sleeve of a gas turbine combustor. Straightening includes receiving the airflow from a plurality of air inlets in a wall of the flow sleeve into the air passage, receiving the airflow at an upstream vane portion of an airflow guide vane, and turning the airflow from the upstream vane portion to a downstream vane portion of the airflow guide vane. The upstream and downstream vane portions are oriented at an angle relative to one another. Straightening also includes discharging the airflow from the airflow guide vane with a substantial reduction of swirl in the airflow.

Problems solved by technology

Unfortunately, flow disturbances may be created as the compressed air flows through the annular gap, thereby decreasing 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

Examples

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Embodiment Construction

[0023]One or more specific embodiments of the present invention will be described below. In an effort to provide a concise description of these embodiments, all features of an actual implementation may not be described in the specification. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure.

[0024]When introducing elements of various embodiments of the present invention, the articles “a,”“an,”“the,” and “said” are intended to mean that ther...

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Abstract

A 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

BACKGROUND OF THE INVENTION[0001]The subject matter disclosed herein relates to combustion chambers, and, more particularly, to flow control within gas turbine engines.[0002]Various combustion systems include combustion chambers in which fuel and air combust to generate hot gases. For example, a gas turbine engine may include one or more combustion chambers that are 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 combustion chamber may include one or more fuel nozzles, a combustion zone within a combustion liner, a flow sleeve surrounding the combustion liner, and a gas transition duct. Compressed air from the compressor flows to the combustion zone through a gap between the combustion liner and the flow sleeve. The flow of the compressed air may include a rotating or circumferential swirl component. Unfortunately, flow disturbances may be created as the compressed air fl...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F23R3/16
CPCF23R3/002Y02T50/675F23R2900/03043F23R3/48Y02T50/60
Inventor MELTON, PATRICK BENEDICTCIHLAR, DAVID WILLIAMROHRSSEN, ROBERT JOSEPHKHAN, ABDUL RAFEY
Owner GENERAL ELECTRIC CO
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