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Turbine fuel nozzle having premixer with auxiliary vane

A technology of fuel nozzle and fuel injection, which is applied in the direction of turbine/propulsion fuel delivery system, machine/engine, gas fuel burner, etc., and can solve problems such as combustion heat damage

Inactive Publication Date: 2010-11-24
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Also, flames sometimes form on or near surfaces, which can also cause damage due to the heat of combustion

Method used

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  • Turbine fuel nozzle having premixer with auxiliary vane
  • Turbine fuel nozzle having premixer with auxiliary vane
  • Turbine fuel nozzle having premixer with auxiliary vane

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Embodiment Construction

[0101] One or more specific embodiments of the invention are described below. In an effort to provide a concise description of these embodiments, all features of an actual implementation may not be described in the specification. It should be recognized that in the development of any of these actual implementations, as in any engineering or design project, many implementation-specific decisions must be made to achieve the developer's specific goals, such as compliance with system-related and business-related constraints , which may vary from one implementation to another. Furthermore, it should be appreciated that such a development effort might be complex and time consuming, but would nevertheless be a matter of routine design, fabrication, and production for those of ordinary skill having the benefit of this disclosure.

[0102] When introducing elements of various embodiments of the present invention, the words "a", "an", "the" and "said" are intended to mean that there ar...

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PUM

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Abstract

The invention relates to a turbine fuel nozzle having a premixer with an auxiliary vane, particularly to a system (100) including a gas turbine engine (118) which includes a combustor (120) and a fuel nozzle (144) in the combustor (120), wherein the fuel nozzle (144) includes a first swirl vane (176) in an air flow (220) and a second auxiliary vane (222) extending out of a surface (216) of the first swirl vane (176), wherein the fuel flow path extends to a fuel port (188) in the second auxiliary vane (222) from the first swirl vane (176) and the second auxiliary vane (222) and the fuel port (188) is introduced to the air flow path (220).

Description

technical field [0001] The subject matter disclosed herein relates to fuel nozzles for gas turbine engines. More specifically, the disclosed subject matter relates to premixers in fuel nozzles. Background technique [0002] A gas turbine engine combusts a mixture of fuel and air to produce hot combustion gases, which in turn drive one or more turbines. Specifically, the hot combustion gases rotate turbine blades, which drive a shaft to rotate one or more loads, such as an electrical generator. As is recognized, a flame is formed in a combustion zone with a combustible mixture of fuel and air. Unfortunately, it is possible for the flame to travel upstream from the combustion zone into the fuel nozzles, which can cause damage due to the heat of combustion. This phenomenon is commonly referred to as flashback. Likewise, flames sometimes form on or near surfaces, which can also cause damage due to the heat of combustion. This phenomenon is commonly referred to as flame hold...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/22F01D9/02F23D14/48
CPCF23G2201/40F23G2206/203F23G2201/303F23G5/027F23R3/286Y02E20/12F23C2900/07001F23G2206/202F23C2900/99011F23R2900/00002
Inventor V·纳卡尼
Owner GENERAL ELECTRIC CO