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Multipurpose gas turbine combustor secondary fuel nozzle flange

A technology of fuel nozzles and flanges, which is applied in the field of gas turbine combustors, and can solve problems such as component scrapping and complex design of secondary fuel nozzle flanges

Inactive Publication Date: 2012-07-11
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] Existing secondary fuel nozzle flange designs caused various field problems and component failures due to issues related to fuel flow
Many of these problems are due to the complex design of the secondary fuel nozzle flange, which in turn dictates both straight and curved concentric fuel-supply piping as well as welding, oblique hole drilling, and loose tolerances involved in machining, all of which Proof can cause problems

Method used

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  • Multipurpose gas turbine combustor secondary fuel nozzle flange
  • Multipurpose gas turbine combustor secondary fuel nozzle flange
  • Multipurpose gas turbine combustor secondary fuel nozzle flange

Examples

Experimental program
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Effect test

Embodiment Construction

[0057] first reference figure 1 , a two-stage (premix / diffusion), gas-only, secondary fuel nozzle assembly 10 according to known construction is typically disposed within a burner central body (not shown) which also houses the surrounding An annular array of primary nozzles with a centered secondary nozzle.

[0058] For burners with secondary fuel nozzles (as in 10) during secondary (or shift) combustion, fuel is supplied by diffuser duct P1 to maintain the flame, and by duct P2 to maintain a premixed flame, diffuser duct P1 and conduit P2 are arranged concentrically relative to each other at the inlet of the secondary fuel nozzle assembly 10 .

[0059] The secondary fuel nozzle assembly 10 includes an outer sleeve 12 and an inner concentrically disposed hollow core 14 having a central bore forming a premix fuel passage 16 . The radial gap between the core 14 and the sleeve 12 provides a diffusion fuel passage 18 therebetween. A plurality of axial air passages 20 are formed...

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PUM

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Abstract

The present invention relates to a multipurpose gas turbine combustor secondary fuel nozzle flange. One exemplary embodiment of a fuel nozzle flange (44) includes an elongated flange body (46) including a radial mounting flange (50) at an aft end thereof and a face surface at a forward end thereof. The flange body (46) has a first, axially-oriented through-bore (54) adapted to receive a first fuel supply pipe (70) at the forward end; a second, radially-oriented bore (60) intersecting the first axially-oriented bore and adapted to receive a second fuel supply pipe (72); and a third axially-oriented through-bore (62) adapted to receive one end of a flame detector device (64) at the forward end.

Description

technical field [0001] The present invention relates to gas turbine combustor technology, and more particularly, to fuel nozzle flange structures for supporting nozzles, flame detectors, and ducts or manifolds that supply fuel and air to the nozzles. Background technique [0002] Existing secondary fuel nozzle flange designs have caused various field problems and component failures due to problems associated with fuel flow. Many of these problems are due to the complex design of the secondary fuel nozzle flange, which in turn dictates both straight and curved concentric fuel-supply piping as well as welding, oblique hole drilling, and loose tolerances involved in machining, all of which Proof can cause problems. [0003] There has been a desire for a less complex secondary fuel nozzle flange configuration that not only eliminates or reduces the problems heretofore experienced with conventional flange configurations, but also with respect to the transition between transfer a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23D14/48
CPCF23R3/36F23R3/343F23R3/28
Inventor K·卡利斯瓦兰N·萨亚S·A·马里高达
Owner GENERAL ELECTRIC CO