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Passive air-fuel mixing prechamber

A pre-combustion chamber and fuel technology, applied in the direction of combustion chamber, continuous combustion chamber, turbine/propellant fuel delivery system, etc.

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

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Problems solved by technology

Also, since typical fuel injection strategies are designed around a narrower fuel range, any additional circuits would only increase the ability to operate on an otherwise narrower fuel range (now centered at different LHVs)

Method used

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  • Passive air-fuel mixing prechamber

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Experimental program
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Embodiment Construction

[0060]The embodiments described herein serve to address the challenge of fuel flexible premixing in gas turbine combustion systems by enabling the fuel injection and premixing process to be more consistent over a wide range of fuel LHV and thus fuel volumetric flow rates . In virtually all gas turbine combustion system premixer designs, pressure drop occurs in the gas flow path, usually across one or more swirlers, vanes or orifices. In one design approach, the pressure drop across the fuel injection orifice is designed to approximately match the pressure drop on the air side. In this way, any sound disturbance in the combustion system affects both the air flow and the fuel flow equally; therefore, the fuel / air ratio remains somewhat constant regardless of sound pressure fluctuations. However, if a new fuel with a strongly different LHV is introduced, the change in fuel injection pressure drop will cause the system to become unbalanced, among other effects.

[0061] figure...

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PUM

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Abstract

The invention relates to a passive air-fuel mixing prechamber. Specifically, a gas turbine combustion system passive air-fuel mixing prechamber (10) includes one or more fuel passages (20). Each fuel passage (20) includes at least one downstream fuel injection orifice (22). One or more fluid conduits (14) connect an upstream portion of at least one fuel passage with one or more air passages (18) such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu / scf to about 900 Btu / scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits (14). The effective area of each fluid conduit (14) relative to the corresponding fuel (20) and air passages (18) is dependent upon the desired fuel LHV operating range.

Description

[0001] Statement on government-funded research and development [0002] This invention was made with US Government support under Contract No. DE-FC26-08NT05868. The government has certain rights in this invention. technical field [0003] The present invention relates generally to gas turbine combustion systems, and more particularly to passive air-fuel mixing pre-chambers that enable wider fuel flexibility in gas turbine combustion systems. Background technique [0004] Fuel flexibility in lean premixed combustion systems is an important challenge for gas turbines as end users expect to utilize a variety of available fuel sources other than natural gas. These various alternative fuels have different combustion characteristics, and availability and composition vary seasonally. A truly fuel flexible combustion system must be able to adapt to these changes (with ideally only changes in fuel control settings). [0005] Modern gas turbines operating on gaseous fuels, most co...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/22
CPCF23R3/286F05D2260/14F23R3/36F23D2900/14004Y02T50/678F23R3/14F23D2900/14701F23R2900/00002F02C3/14
Inventor J·T·赫邦M·P·贝斯普夫卢格G·A·贝内特F·陶G·乔蒂普拉萨德
Owner GENERAL ELECTRIC CO