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Gas turbine combustion chamber

A gas turbine and combustor technology, applied in the field of combustors, can solve problems affecting combustion stability and completeness, and low fuel-lean combustion stability

Inactive Publication Date: 2005-08-31
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] Due to the fact that the stability of lean combustion is lower than that of the proper stoichiometric ratio, and after the premixing technology is adopted, the fuel evaporates simultaneously in the process of premixing with air, and the fuel in the combustible air mixture is either in a single-phase state or basically Entering the combustion zone close to the single-phase state has a certain influence on the stable combustion under different oil-gas ratios. When the operating state of the gas turbine changes in a wide range (this is what the user requires), the fuel-air ratio in the combustion chamber is also very large. Changes in a wide range, which may cause too lean combustion in some states, which affects the stability and completeness of combustion, or the leanness of some states is not enough to make the emitted NO X increase, so that the gas engine cannot maintain efficient and stable combustion and low NO in a wide operating range X emission

Method used

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Embodiment Construction

[0019] The gas turbine combustor contains multiple sub-combustors 3 distributed along the circumference, and a fuel-air premixer 5 in the middle of the head of each sub-combustor, with multiple fuel-air premixers around it, and multiple fuel-air premixers. The mixer and the recirculation area formed after it are separated into several areas by the gas film wall structure 9. When the gas turbine is working in various states, it is determined according to the fuel consumption and the range of oil-gas ratio in the combustion area to determine the number of fuel The air premixer feeds the fuel and in the subsequent recirculation zone a lean and stable combustion process. Along with the change of the working state of the gas turbine, the fuel is supplied to part or all of the fuel-air premixer and the combustion process is carried out in the subsequent recirculation zone. In order to achieve low pollution emissions, the temperature of the combustion zone must be controlled within a...

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Abstract

In the present invention, fuel nozzle is set at each combustion chamber and mated fuel-air premixer is also set attaached to the fuel nozzle as an oil injection channel being set in the fuel nozzle; air film wall is set at position between each fuel-air premixer to down stream combustion area and some flame stabilizing devices are set in folloiwng the nozzle.

Description

Technical field [0001] The invention relates to a combustor of a gas turbine, especially for realizing low NO X Dry emissions of CO and CO should provide a combustor with a stable ignition source under low-lean conditions. Background technique [0002] The combustion chamber of the gas turbine includes a plurality of sub-combustion chambers distributed along the circumference. There is a fuel-air premixer in the middle of the head of each sub-combustion chamber, and a plurality of fuel-air premixers are arranged around it. [0003] The premixer includes fuel nozzles, vortex blades, and fuel nozzles. The air passes through the vortex blades to obtain vortex force, and flows out of the premixer at a certain axial and circumferential speed, forming a recirculation zone downstream, and the fuel-air mixture Continuous combustion takes place in the recirculation zone. The premixer is a dual-fuel premixer, and gas or liquid fuel is injected from the nozzle opening before or in o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/00F23R3/28
Inventor 徐义坤崔荣繁陈克杰卫宝华张国华杨茂林赵光武
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION