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Multi-fuel-loop used for premixing synthetic gas/ng dln in nozzle

A fuel and fuel source technology, applied to gas fuel burners, burners, combustion chambers, etc., can solve problems such as reducing emissions

Inactive Publication Date: 2010-12-29
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0009] In addition to these issues, conventional lean premix burners have not achieved the ability to minimize emissions through a perfectly uniform premixing of fuel and air

Method used

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Embodiment Construction

[0049] figure 1 is a section through the combustion apparatus described in U.S. Patent No. 6,438,961, while figure 2 with image 3 Shows details of the air swirler assembly that injects fuel through rotating vanes or swozzles. In practice, an air atomizing liquid fuel nozzle would be mounted in the center of the combustor assembly to provide dual fuel capability; however, this liquid fuel nozzle assembly does not form part of the present invention and has been omitted from illustration for clarity. The burner assembly is divided into four areas according to function, including the inlet flow regulator 1, the air swirler assembly for natural gas fuel injection (called the swirl nozzle assembly) 2, the annular fuel / air mixing passage 3, and the central diffusion flame Natural gas fuel nozzle assembly 4.

[0050] Air enters the burner from a high pressure chamber 6 which surrounds the entire assembly except for the discharge end which enters the reaction zone 5 of the burner....

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Abstract

The invention relates to a multi-fuel-loop used for premixing synthetic gas / NG DLN in nozzle. Concretely, a fuel / air premixer used for a burner in a combustion system of a gas turbine comprises an air inlet (1 and 6), a fixed nozzle geometry structure (4) and a annular mixing channel (3). The fuel / air premixer mixes fuel and air in the annular mixing channel to inject the mixture in a burner reaction area (5). A plurality of fuel sources (21 and 22) are connected with the fixed nozzle geometry structure, and cooperate with the fixed nozzle geometry structure to realize various fuel flow changes such as fuel type change, fuel doping change, volume flow change and pressure ratio change.

Description

technical field [0001] The present invention relates to heavy duty industrial gas turbines, and in particular to burners for industrial gas turbines that include a mixture of multiple gas streams to achieve desired properties such as fuel mixing for emissions, flame holding robustness, and control of combustion oscillations fuel / air premixer. Background technique [0002] Gas turbine manufacturers are currently involved in research and engineering programs to produce new types of gas turbines that will operate efficiently without producing undesirable air-polluting emissions. The main air polluting emissions typically produced by combustion of conventional hydrocarbon fuels by gas turbines are nitrogen oxides, carbon monoxide, and unburned hydrocarbons. It is well known in the art that the oxidation of nitrogen molecules in air engines is largely dependent on the maximum hot gas temperature in the reaction zone of the combustion system. The chemical reaction rate to form n...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23D14/64
CPCF23R3/36F23R3/286
Inventor J·C·因泰尔
Owner GENERAL ELECTRIC CO
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