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
US20120297784A1Inactive Publication Date: 2012-11-29GENERAL ELECTRIC CO
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Patent Information

Authority / Receiving Office
US Β· United States
Patent Type
Applications(United States)
Current Assignee / Owner
GENERAL ELECTRIC CO
Publication Date
2012-11-29
Estimated Expiration
Not applicable Β· inactive patent

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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.
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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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