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Fluid cooled injection nozzle assembly for a gas turbomachine

A fluid cooling, injection nozzle technology, used in turbine/propulsion cooling, engine cooling, engine components, etc., to solve problems such as increasing NOx emissions

Inactive Publication Date: 2011-11-09
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The pilot flame typically burns at a higher temperature than the main and auxiliary flames, which results in increased NO x emission

Method used

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  • Fluid cooled injection nozzle assembly for a gas turbomachine
  • Fluid cooled injection nozzle assembly for a gas turbomachine
  • Fluid cooled injection nozzle assembly for a gas turbomachine

Examples

Experimental program
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Embodiment Construction

[0066] The terms "axial" and "axially" are used in this application to refer to directions and orientations extending substantially parallel to the central longitudinal axis of the center body of the combustor tube assembly. The terms "radial" and "radially" are used in this application to refer to directions and orientations extending substantially normal to the central longitudinal axis of the central body. The terms "upstream" and "downstream" are used in this application to refer to the direction and orientation relative to the axial flow direction of the central longitudinal axis of the centerbody.

[0067] refer to figure 1 , a turbine constructed in accordance with an exemplary embodiment is indicated generally at 2 . The turbine 2 includes a compressor 4 and a combustor assembly 5 having at least one combustor 6 equipped with a fuel nozzle or injection assembly housing 8 . The turbine 2 also includes a turbine 10 . Notably, the disclosed exemplary embodiments describe...

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PUM

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Abstract

The invention relates to a fluid cooled injection nozzle assembly for a gas turbomachine. The turbomachine includes a fluid cooled injection nozzle assembly. The fluid cooled injection nozzle assembly includes an inner conduit portion that includes a body portion having first end portion to a tip end portion. The body portion includes an outer surface and an inner surface. A cooling element extends through the inner conduit portion. The cooling element includes a body element having a first end section that extends to a second end section. The body element includes an outer surface and an inner surface that defines a cooling passage. The outer surface of the body element is spaced from the inner surface of the inner conduit portion to define a return channel. Fluid passing through the cooling passage impinges upon and convectively cools the tip end portion, enters the return channel and is directed out from the nozzle member.

Description

technical field [0001] The presently disclosed subject matter relates to the field of turbomachines, and more particularly, to fluid-cooled injection nozzle assemblies for gas turbines. Background technique [0002] Gas turbine engines typically burn a fuel / air mixture that releases heat energy to create a high temperature gas flow. The high temperature gas stream is delivered to the turbine through the hot gas channel. A turbine converts thermal energy from a high temperature gas stream into mechanical energy that turns the turbine shaft. Turbines are used in a variety of applications, such as powering pumps or generators. [0003] Currently, there is a need for lower turbine emissions. One of the paths to lower emissions is to eliminate the pilot flames that currently exist at the tip portion of the turbine nozzle. The pilot flame typically burns at a higher temperature than the main and auxiliary flames, which results in increased NO x emission. By eliminating the p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/22F02C7/12F23D14/48F23D14/78
CPCF23R3/283
Inventor L·J·斯托亚B·W·罗米
Owner GENERAL ELECTRIC CO