Multi-premixer fuel nozzle

Inactive Publication Date: 2012-02-09
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

As the fuel nozzle count increases, however, the center bodies begin to restrict airflow to the more central nozzles.
This restriction may cause unacceptable variations in the airflow uniformity between the center and outer fuel nozzles and between adjacent nozzles.
This variation may cause uneven fuel air mixing and may result in decreased flame holding margins and non-uniform flame temperatures within the within the combustion chamber.
Further, these uneven temperatures may lead to increased emissions and durability concerns.

Method used

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  • Multi-premixer fuel nozzle
  • Multi-premixer fuel nozzle
  • Multi-premixer fuel nozzle

Examples

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Embodiment Construction

[0015]Referring now to the drawings, in which like numbers refer to like elements throughout the several views, FIG. 1 shows a schematic view of a gas turbine engine 10. As is known, the gas turbine engine 10 may include a compressor 20 to compress an incoming flow of air. The compressor 20 delivers the compressed flow of air to a combustor 30. The combustor 30 mixes the compressed flow of air with a compressed flow of fuel and ignites the mixture. (Although only a single combustor 30 is shown, the gas turbine engine 10 may include any number of combustors 30.) The hot combustion gases are in turn delivered to a turbine 40. The hot combustion gases drive the turbine 40 so as to produce mechanical work. The mechanical work produced in the turbine 40 drives the compressor 20 and an external load 50 such as an electrical generator and the like. The gas turbine engine may use natural gas, various types of syngas, and other types of fuels.

[0016]Other types of gas turbine engines 10 may b...

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Abstract

The present application provides a fuel nozzle for use in a gas turbine. The fuel nozzle may include a mounting flange, a number of premixers attached to each other, and a number of gas pathways extending from the mounting flange to the number of premixers.

Description

TECHNICAL FIELD[0001]The present application relates generally to gas turbine engines and more particularly relates to the use of fuel nozzles with one fuel supply and mounting column and multiple premixers for premixing prior to combustion.BACKGROUND OF THE INVENTION[0002]Current fuel nozzle designs for gas turbine combustion systems generally include one central mounting and fuel supply center body per fuel nozzle or a separate fuel supply. Several fuel and air circuits may be contained within the center body. When the fuel nozzle counts is in the range of about four to six nozzles, current combustion chambers with the center bodies generally present no problem from the standpoint of distributing airflow to the more central nozzles.[0003]As the fuel nozzle count increases, however, the center bodies begin to restrict airflow to the more central nozzles. This restriction may cause unacceptable variations in the airflow uniformity between the center and outer fuel nozzles and betwee...

Claims

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Application Information

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IPC IPC(8): F23R3/14F23R3/28
CPCF23C7/004F23C2900/07001F23R3/286F23D2900/14021F23D14/64
InventorMCMAHAN, KEVIN WESTONVENKATARAMAN, KRISHNA KUMARBERRY, JONATHAN DWIGHTSTRYAPUNINR, SERGEY ALEKSANDROVICH
OwnerGENERAL ELECTRIC CO