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Integrated fuel nozzle IFC

A technology of fuel nozzles and regulators, which can be used in combustion chambers, combustion methods, combustion equipment, etc., can solve the problem of high cost

Inactive Publication Date: 2013-06-19
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method of manufacturing the fuel nozzle-IFC assembly is costly and since it relies on proper positioning of several components, there are unwanted deviations during assembly that cause variations in the air flow into the nozzle

Method used

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  • Integrated fuel nozzle IFC
  • Integrated fuel nozzle IFC
  • Integrated fuel nozzle IFC

Examples

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Embodiment Construction

[0016] Such as figure 1 Shown is a cross-sectional view of a portion of a gas turbine 10 extending about a gas turbine axis 12 . Liner 14 connected to transition piece 16 directs combustion gases from combustor 20 to turbine 18 . The combustor 20 employs one or more fuel nozzles 22 disposed within the combustor to deliver fuel and air to a combustion zone 24 for ignition and combustion. Fuel is provided to each fuel nozzle 22 by a fuel source (not shown). The bushing 14 is disposed within or extends through the diffuser housing 26 and, as in figure 1 The bushing 14 in the example shown includes an inner bushing 28 and an outer bushing 30 defining a bushing channel 32 in the middle. The outboard liner 30 includes at least one outboard liner opening 34 that allows air to enter the liner passage 32 .

[0017] The combustor 20 includes a forward casing 36, which in this embodiment is connected to the liner 14, and an end cover 38 coupled to the forward casing by retaining hard...

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PUM

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Abstract

Disclosed is a fuel nozzle for a gas turbine including a center body defining one or more fuel passages and an inlet flow conditioner. The inlet flow conditioner includes a substantially tubular hub, a substantially tubular outer land, and a plurality of spars extending radially outwardly from the hub to the outer land. The plurality of spars together with the hub and outer land define a plurality of fluid flow passages capable of removing circumferential and radial variation from fluid flow entering the fuel nozzle. The inlet flow conditioner is formed as a single unitary component. Further disclosed is a method of operating the gas turbine including the fuel nozzle.

Description

technical field [0001] The present invention generally relates to rotary machines. More specifically, the present invention relates to fuel nozzles for gas turbine engines. Background technique [0002] Gas turbines typically include a combustor in which a fuel-air mixture is ignited to generate a combustion gas flow that is passed to the turbine. The combustor typically includes one or more fuel nozzles that provide an air-fuel mixture to the combustion chamber for ignition. Compressed air is typically provided by a compressor to the fuel nozzles where it mixes with fuel. Additionally, the combustor may include an inlet flow conditioner, or IFC, to smooth out radial and circumferential variations in air flow entering the fuel nozzle. This allows the nozzle to mix air and fuel uniformly and predictably in the combustor to precisely achieve the desired fuel-to-air ratio. Precise control of the fuel-to-air ratio is required to ensure gas turbines meet emissions and perform...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/04F23R3/26F23R3/14
CPCF23R3/14F23R3/54F23R3/28F23R3/10F23R3/16F23R2900/00017
Inventor T·E·约翰逊J·B·麦克米兰
Owner GENERAL ELECTRIC CO
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