Combustion system for a gas turbine engine

Inactive Publication Date: 2015-06-11
SIEMENS AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a way to reduce emissions in combustion engines. It involves using a pilot fuel injector and multiple main injectors to mix fuel and air in a combustion chamber. The method also includes creating vortices downstream from where the fuel and air are ignited to further reduce emissions. This can help to improve the engine's efficiency and reduce harmful emissions.

Problems solved by technology

For example, elevated levels of NOx can result from elevated combustion temperatures and / or an extended residence time of the combustion products in the combustor, and elevated levels of CO can result from reduced combustion temperatures and / or insufficient residence time in the combustor.

Method used

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  • Combustion system for a gas turbine engine
  • Combustion system for a gas turbine engine
  • Combustion system for a gas turbine engine

Examples

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Embodiment Construction

[0028]In the following detailed description of the preferred embodiment, reference is made to the accompanying drawings that form a part hereof, and in which is shown by way of illustration, and not by way of limitation, a specific preferred embodiment in which the invention may be practiced. It is to be understood that other embodiments may be utilized and that changes may be made without departing from the spirit and scope of the present invention.

[0029]In accordance with an aspect of the invention, a configuration for a combustor in a gas turbine engine is provided that reduces low temperature areas of a combustion zone with a resulting reduction in carbon monoxide (CO) and / or NOx in the working gas provided to a turbine section of the engine. In particular embodiments, mixing structure is provided for inducing increased mixing of gases at specific predetermined locations within a combustion chamber of the combustor to maintain combustion zone regions associated with the predeter...

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Abstract

A combustor for a gas turbine engine includes a pilot fuel injector and a plurality of circumferentially located main injectors for injecting fuel and air into a combustion chamber defined by a liner wall of a combustor basket. A combustion zone is located in the combustion chamber where the fuel and air are ignited to produce hot combustion gases. A plurality of vortex generators are located in circumferentially spaced relation on the liner wall and comprise structures extending radially inward into the combustion chamber to create vortices at predetermined circumferential locations downstream from where the fuel and air are ignited to effect a reduction in emissions of the combustion gases.

Description

FIELD OF THE INVENTION[0001]The present invention relates to gas turbine engines and, more particularly, to a combustion system for a gas turbine engine in which the combustion system is configured to produce reduced emissions.BACKGROUND OF THE INVENTION[0002]Combustion turbines, such as gas turbine engines, generally comprise a compressor section, a combustor section, a turbine section and an exhaust section. In operation, the compressor section can induct and compress ambient air. The combustor section generally may include a plurality of combustors for receiving the compressed air and mixing it with fuel to form a fuel / air mixture. The fuel / air mixture is combusted by each of the combustors to form a hot working gas that may be routed to the turbine section where it is expanded through alternating rows of stationary airfoils and rotating airfoils and used to generate power that can drive a rotor. The expanding gas exiting the turbine section can be exhausted from the engine via t...

Claims

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Application Information

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IPC IPC(8): F23R3/58
CPCF23R3/58F23R3/06F23R3/16F23R2900/00014F23R2900/03045
InventorSCHILDMACHER, KAI-UWEYOU, DANNINGWORZ, ULRICHRAMIER, STEPHEN A.
OwnerSIEMENS AG