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Combustion gas turbine combustion chamber head structure and combustion organization method of combustion gas turbine combustion chamber

A technology for gas turbines and combustion chambers, applied in combustion methods, combustion chambers, continuous combustion chambers, etc., can solve problems such as limited potential, flat increase in nitrogen oxide emission levels, failure to meet emission standards, etc. The effect of saving cooling area and cooling structure design

Active Publication Date: 2015-04-29
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Comparing the latest combustion chamber products in the 1990s and the present in the world, it can be seen that the average outlet temperature has increased by about 200°C. Although the combustion chamber has undergone a series of optimizations and improvements, the emission level of nitrogen oxides has remained the same or even slightly increased. This shows that the current combustor design structure has limited potential when targeting future higher parameter combustors, and faces the risk of not meeting emission standards

Method used

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  • Combustion gas turbine combustion chamber head structure and combustion organization method of combustion gas turbine combustion chamber
  • Combustion gas turbine combustion chamber head structure and combustion organization method of combustion gas turbine combustion chamber
  • Combustion gas turbine combustion chamber head structure and combustion organization method of combustion gas turbine combustion chamber

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Embodiment 1

[0030] refer to Figures 1 to 6 As shown, the gas turbine combustor head structure of the present invention includes a head end plate 1 , a central swirl nozzle module 10 , a plurality of high-speed jet nozzle modules 11 and a plurality of low-speed jet nozzle modules 12 . The central swirl nozzle module 10 is installed on the head end plate 1 and is located at the center of the head end plate 1 . A plurality of high-speed jet nozzle modules 11 and a plurality of low-speed jet nozzle modules 12 are also mounted on the head end plate 1 and arranged around the central swirl nozzle module 10 to form an inner nozzle circle and an outer nozzle circle. The head end plate 1 is provided with a plurality of fuel intake passages for supplying fuel to the central swirl nozzle module 10 , the high-speed jet nozzle module 11 and the low-speed jet nozzle module 12 . Wherein, the average equivalent ratio of the high-speed jet nozzle module 11 is smaller than the average equivalent ratio of ...

Embodiment 2

[0040] The head structure of the gas turbine combustor in this embodiment includes a head end plate 1 , a central swirl nozzle module 10 , a plurality of high-speed jet nozzle modules 11 and a plurality of low-speed jet nozzle modules 12 . The central swirl nozzle module 10 is installed on the head end plate 1 and is located at the center of the head end plate 1 . A plurality of high-speed jet nozzle modules 11 and a plurality of low-speed jet nozzle modules 12 are also mounted on the head end plate 1 and arranged around the central swirl nozzle module 10 to form an inner nozzle circle and an outer nozzle circle. The head end plate 1 is provided with a plurality of fuel intake passages for supplying fuel to the central swirl nozzle module 10 , the high-speed jet nozzle module 11 and the low-speed jet nozzle module 12 . Wherein, the central swirl nozzle module 10, the high-speed jet nozzle module 11, and the low-speed swirl nozzle module 12 are all the same as in Embodiment 1, ...

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Abstract

The invention relates to the technical field of a combustion gas turbine combustion chamber and discloses a combustion gas turbine combustion chamber head structure. The combustion gas turbine combustion chamber head structure comprises a head end plate, a central whirl nozzle module, a plurality of high-speed injection nozzle modules and a plurality of low-speed injection nozzle modules, wherein the central whirl nozzle module is arranged on the head end plate; the plurality of high-speed injection nozzle modules and the plurality of low-speed injection nozzle modules are arranged around the central whirl nozzle module to form an inner nozzle ring and an outer nozzle ring. Due to the fact that the combustion gas turbine combustion chamber head structure adopts the plurality of high-speed injection nozzle modules and the plurality of low-speed injection nozzle modules, a local continuous distinguishing and re-burning distributive flame is formed, the flame peak temperature is reduced at higher outlet average temperature, and generation of nitrogen oxides is inhibited. Meanwhile, the invention also provides a combustion organization method of the combustion gas turbine combustion chamber.

Description

technical field [0001] The invention relates to the technical field of gas turbine combustors, in particular to a gas turbine combustor head structure and a combustion organization method thereof. Background technique [0002] For industrial heavy-duty gas turbines, the development goals for decades have always been higher average temperature of the combustion chamber outlet (standardized gas turbine technical level) and lower pollutant emissions; the above technical indicators are closely related to the combustion chamber and contradict each other, higher The average temperature at the outlet of the combustion chamber means that more fuel participates in the combustion process, and the average temperature in the combustion chamber is higher. Nitrogen oxides, which are the main pollutants in the combustion chamber, are closely related to the thermal process inside the combustion chamber. The basic function of the gas turbine combustor is to convert the chemical energy in the...

Claims

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Application Information

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IPC IPC(8): F23R3/42
Inventor 方子文吕煊李珊珊张永良陈伟
Owner CHINA UNITED GAS TURBINE TECH CO LTD