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Pre-mixed fuel spray nozzle for gas turbine and combustor

A technology of fuel nozzles, gas turbines, applied in the field of combustion chambers

Active Publication Date: 2018-05-11
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

While flame shape and properties can be changed, usually only radial properties such as fuel distribution or swirl can be changed

Method used

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  • Pre-mixed fuel spray nozzle for gas turbine and combustor
  • Pre-mixed fuel spray nozzle for gas turbine and combustor
  • Pre-mixed fuel spray nozzle for gas turbine and combustor

Examples

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Embodiment Construction

[0040] The present invention will be described in more detail with reference to the following examples, but it should be understood that the present invention is not considered limited to these examples.

[0041] Referring now to the drawings, the same reference numerals refer to the same elements throughout the multiple figures, figure 1 Shown therein is a combustion chamber 10 with premix nozzles 12, 22 according to a first exemplary embodiment of the present invention. The main components of the combustion chamber 10 include a combustion chamber shell 14, an end cover 16, a cap 18, a reaction zone 20, a central premix fuel nozzle 12 and a plurality of peripheral premix fuel nozzles 22. The nozzles 12 and 22 are used to inject the air-fuel mixture 21 into the reaction zone 20.

[0042] Such as Figure 2 to Figure 9 As can be best seen in, the premixed fuel nozzles 12, 22 generally include a fuel and air premixer 23, a nozzle head 24, and a burner tube 25. It is worth noting that...

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PUM

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Abstract

The invention relates to a pre-mixed fuel spray nozzle for a gas turbine and a combustor. The pre-mixed fuel spray nozzle comprises a spray nozzle head, and the spray nozzle head comprises an outer body and one or more sections. The outer body is provided with an outer body outer surface facing the downstream end of a spray combustion pipe, and the outer body outer surface has a cross section smaller than that of the spray combustion pipe. The one or more sections extend outwards in a radial mode in the radial direction from the inner wall, facing the spray combustion pipe, of the outer body.Each section is provided with a near end arranged adjacent to the outer body outer surface and a far end arranged towards the spray combustion pipe, and each section is further provided with a sectiondownstream surface facing the downstream end of the spray combustion pipe and inclining relative to the longitudinal axis of the spray combustion pipe by an angle. When the gas turbine runs, the axial flow field of an air and fuel mixture flows around the spray nozzle head through the spray combustion pipe, and two or more return areas with different radial dimensions are formed on the spray nozzle head through the sections so that high flame stabilizing and flame spraying capacities can be provided.

Description

Technical field [0001] The invention relates to a combustor for a gas turbine. More particularly, the present invention relates to an improved fuel nozzle for the combustor of a gas turbine. Background technique [0002] A typical gas turbine commonly used in power generation uses a combustion chamber to generate high-pressure and high-temperature combustion gas to perform work. Such a gas turbine generally includes an intake section, a compressor section, a combustion section, a turbine section, and an exhaust section. More specifically, the compressor section supplies the compressed working fluid to the combustion section. The compressed working fluid and fuel are mixed and combusted in the combustion section to generate high-pressure and high-temperature combustion gases. The combustion gas flows into the turbine section, where the combustion gas expands to perform work. The expanded gas is released in the exhaust section. [0003] The combustion section includes one or mor...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/20F23R3/28F23R3/38F23R3/52
CPCF23R3/20F23R3/286F23R3/38F23R3/52F23R3/343F02C3/14F05D2220/32
Inventor R·布兰德J·巴塔廖利张珊珊查筱晨
Owner CHINA UNITED GAS TURBINE TECH CO LTD