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turbine fuel nozzle

A technology of fuel nozzles and turbines, which is applied in the direction of turbine/propulsion fuel delivery system, fuel control of turbine/propulsion device, gas fuel burner, etc., and can solve problems such as reduction

Inactive Publication Date: 2011-11-30
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Traditional approaches to reducing NOx emissions from combustion turbines (water and steam injection) are limited in their ability to achieve the extremely low levels required in many locations

Method used

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Examples

Experimental program
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Effect test

Embodiment Construction

[0068] see figure 1 , a turbine constructed in accordance with an exemplary embodiment is shown generally at 2 . The turbine 2 includes a compressor 4 and a plurality of circumferentially spaced combustors, one of which is shown at 6 . Combustor 6 includes a combustor 8 that directs hot gases to a turbine 10 operatively coupled to compressor 4 via a common compressor / turbine shaft or rotor 12 .

[0069] In operation, air flows through the compressor 4 such that the compressed air is supplied to the combustor 6 . Fuel is directed to the combustion chamber 8, mixed with air, and ignited to form combustion gases. The combustion gases are channeled to a turbine 10 where the thermal energy of the gas flow is converted into mechanical rotational energy. Turbine 10 is rotatably coupled to and drives shaft 12 . It should be appreciated that, as used herein, the term "fluid" includes any medium or material that flows and is not limited to gas and / or air. Furthermore, the term "fuel"...

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PUM

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Abstract

The present invention relates to turbine fuel nozzles. Specifically, a turbomachine includes a compressor, a turbine operably coupled to the compressor, and a combustor fluidly coupling the compressor and the turbine. The combustor includes at least one fuel nozzle. The at least one fuel nozzle includes a flow passage including a body having a first end extending to a second end through at least one flow conduit having a flow region. A fuel inlet is provided at the first end of the body. The fuel inlet is configured to receive at least one fuel. A fuel outlet is provided at the second end of the body. A control flow passage is fluidly connected to the body between the first end and the second end. The control flow passage is constructed and arranged to deliver a control flow into the fuel nozzle. The control flow establishment forms a selectively variable effective flow area of ​​the flow channel.

Description

technical field [0001] The subject matter disclosed herein relates to the field of turbomachines, and more particularly to fuel nozzles for turbomachines. Background technique [0002] A turbine generally includes a compressor, a combustor, and a turbine. In operation, air flows through the compressor, is compressed and supplied to the combustors. Fuel is also directed to the combustor, mixed with compressed air, and ignited to form combustion gases. Combustion gases are channeled to a turbine. The turbine converts thermal energy from the combustion gases into mechanical rotational energy, which is used to power a compressor and produce useful work, such as to operate an electrical generator. Conventional turbines are designed to operate on a specific fuel or family of fuels. [0003] Regulatory requirements for low emissions from gas turbine power plants have become more stringent in recent years. Environmental agencies around the world are now increasingly demanding e...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/26F23D14/48
CPCF23D11/24F23D11/38F23R3/28F23D2900/14482
Inventor A·R·罕K·K·辛赫
Owner GENERAL ELECTRIC CO