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A gas turbine combustor nozzle device

A nozzle device, gas turbine technology, applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of poor combustion stability, smaller load adjustment range, tempering, etc., and achieve the effect of stable combustion

Active Publication Date: 2020-11-24
DONGFANG TURBINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] DLN technology has incomparable advantages in pollutant control, but it also brings problems such as poor combustion stability, flashback, smaller load adjustment range, and prone to combustion oscillations.

Method used

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  • A gas turbine combustor nozzle device
  • A gas turbine combustor nozzle device
  • A gas turbine combustor nozzle device

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Experimental program
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Embodiment 1

[0035] Such as figure 1 , figure 2 As shown, in this embodiment, a gas turbine combustor nozzle device is specifically provided, including an end cover 1, the end cover 1 has a circular structure, and the end cover 1 is used as the main body of the gas turbine combustor nozzle device, which is assembled on the gas turbine Combustion and pressure cylinder block and act on fuel graded supply system.

[0036] It also includes a plurality of independent fuel chambers arranged inside the end cover 1 , and each fuel chamber is divided into a main fuel chamber and an on-duty fuel chamber 13 . In this embodiment, there are two main fuel chambers and one on-duty fuel chamber 13 , wherein the two main fuel chambers are the first main fuel chamber 14 and the second main fuel chamber 16 . Preferably, the first main fuel chamber 14, the second main fuel chamber 16 and the on-duty fuel chamber 13 are all provided with annular cavities, and the three are arranged in concentric rings insid...

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PUM

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Abstract

The invention discloses a gas turbine combustor nozzle device, which belongs to the technical field of gas turbines. It includes an end cover and a plurality of independent fuel chambers arranged inside the end cover. The fuel pipes are connected with each fuel chamber respectively, and the other side is arranged with a nozzle group and a nozzle group, and the nozzle group and the nozzle group are respectively arranged on different fuel chambers; The hole group includes a plurality of first fuel injection holes communicated with the fuel chamber; the nozzle group includes a plurality of main fuel nozzles communicated with the fuel chamber, and each of the main fuel nozzles is provided with several second fuel nozzles. In order to achieve the purpose of fuel graded entry into the swirler and flame tube, to achieve stable combustion, to promote uniform mixing of fuel and air, and to suppress the occurrence of combustion oscillations.

Description

technical field [0001] The invention belongs to the technical field of gas turbines, and in particular relates to a gas turbine combustion chamber nozzle device. Background technique [0002] In order to achieve stable combustion and low pollution emissions in the combustor of gas turbines, the general practice in the design of combustors for heavy-duty gas turbines in the world is to adopt a combined combustion method of diffusion combustion and premixed combustion in the combustor. [0003] Dry low NOx (DLN) combustion technology is a mature technology commonly used by heavy-duty gas turbines in the world today to control pollutant emissions. The most critical technology is to achieve uniform mixing of fuel and air and dilute-phase premixed combustion. The most essential advantage of dilute-phase premixed combustion is its low flame temperature, which directly affects the formation of NOx. [0004] DLN technology has incomparable advantages in pollutant control, but it al...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38
CPCF23R3/38
Inventor 杨安建田晓晶凤云仙冯珍珍刘维兵艾松
Owner DONGFANG TURBINE CO LTD