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Premix fuel nozzle internal flow path enhancement

A fuel injection and nozzle technology, applied in the field of gas turbine fuel nozzle structure

Inactive Publication Date: 2011-09-14
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Additionally, the plug causes an unnecessary internal "step" in the flow channel

Method used

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  • Premix fuel nozzle internal flow path enhancement
  • Premix fuel nozzle internal flow path enhancement
  • Premix fuel nozzle internal flow path enhancement

Examples

Experimental program
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Embodiment Construction

[0020] See figure 1 The gas turbine 10 includes a compressor housing 12 (partially shown), a plurality of combustors 14 (one shown), and a turbine inlet section shown here through a single turbine nozzle blade 16. Although not specifically shown, the turbine blades are drivingly connected to the compressor rotor along a common axis. The compressor pressurizes the inlet air, which then turns and flows in the opposite direction (as indicated by the fluid arrow) into the combustor 14, where it is used to cool the combustor and provide air for the combustion process.

[0021] More specifically, each combustor 14 includes a substantially cylindrical combustor housing 18 that is fixed to the turbine housing 20 by, for example, bolts 22. The front end of the burner housing is closed by an end cover assembly 24. The end cover assembly 24 may include conventional supply pipes, manifolds, and related valves (generally shown at 26), etc., for supplying gas, liquid fuel, and Air (and water ...

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PUM

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Abstract

The invention relates to a premix fuel nozzle internal flow path enhancement. A nozzle 28 for gas turbine includes a tubular nozzle body 30; and a plurality of hollow fuel injection pegs 42 extending radially from the tubular nozzle body at a location between forward and aft ends of the tubular nozzle body; wherein each of the plurality of hollow fuel injection pegs has an external tear-drop cross-sectional shape, and a fuel passage 68 in each of the hollow injection pegs has a substantially matching internal tear-drop cross-sectional shape.

Description

Technical field [0001] The present invention relates to gas turbine combustor technology, and more specifically, to a gas turbine fuel nozzle structure with an improved internal flow channel design. Background technique [0002] In a typical "can-ring" type gas turbine combustor device, several combustors are arranged in an annular array around the axis of the turbine rotor, and the combustion gas is supplied to the first stage of the turbine. The compressor pressurizes the inlet air, which is then diverted (or vice versa) to the combustor where it is used to cool the hot gas path components and provide air for the combustion process. Each combustor assembly includes a generally cylindrical combustor (including a combustion chamber), a fuel injection system, and a transition piece or tube that directs the hot combustion gas flow from the combustor to the turbine section inlet. This type of gas turbine may generally include 6, 10, 14, or 18 combustors arranged around the axis of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23D14/48
CPCF23R3/286F23D2900/00008F23D2900/14004F23R3/14
Inventor J·T·斯图尔特G·E·詹森M·W·平森J·P·图马J·K·佩林加特
Owner GENERAL ELECTRIC CO