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A premixing nozzle for a gas turbine combustor

A gas turbine, pre-mixing technology, applied in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve limited problems, achieve the effects of reducing low-speed areas, preventing backfire, and suppressing the existence of local high temperatures

Active Publication Date: 2017-09-15
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since the hub only increases the passage for gas circulation within the height range of the swirling blades, and the passage provided by it is a straight passage, the effect of reducing the low-velocity zone is very limited, and the problem of tempering still exists

Method used

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  • A premixing nozzle for a gas turbine combustor
  • A premixing nozzle for a gas turbine combustor
  • A premixing nozzle for a gas turbine combustor

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Embodiment Construction

[0017] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.

[0018] figure 1 , figure 2 It is a schematic diagram of the structure and principle of a premixing nozzle of a gas turbine combustor provided by the present invention. The nozzle includes an axial swirler 1, a tapered central body 2, and a mixing section 3, wherein the axial swirler 1 is provided with an outer layer air inlet 11, swirl vanes 12 and a swirler outer wall 13, The outer layer fuel outlet 122 and the outer layer fuel passage 121 are arranged on the swirl blade 12, and the central gas fuel inlet 21 is arranged on the tapered central body 2, and on the outside of the tapered central body 2, the axial swirler 1 is provided with a tapered annular tube 4 arranged coaxially with the tapered central body 2, the inner wall of the tapered annular tube and the outer wall of the tapered central body 2 form an ...

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Abstract

A premixing nozzle of a combustion chamber of a gas turbine relates to a nozzle structure with axial swirl. The technical solution of the present invention is that a tapered annular pipe is arranged between the tapered central body and the axial swirler, and an annular passage is formed between the tapered annular pipe and the tapered central body, and the front end of the annular passage There is an inner layer air inlet, and guide vanes are arranged in the annular channel, and the guide vanes are provided with an inner layer fuel outlet and an inner layer fuel channel, and the inner layer fuel channel communicates with the central gas fuel inlet and the outer layer fuel channel. The present invention aims at the characteristics that premixed combustion is prone to backfire due to the existence of the low-velocity zone, and effectively eliminates the The low-velocity zone at the center caused by the centrifugal force of swirler rotation can prevent the flashback problem of premixed combustion, prolong the life of premixed nozzles, and reduce the use and maintenance costs of gas turbine combustors.

Description

technical field [0001] The invention relates to a gas turbine combustor structure using gas fuel premixed combustion, in particular to a nozzle structure with axial swirl flow. Background technique [0002] Due to the increasingly stringent requirements for environmental protection, premixed combustion is increasingly used in gas turbine combustors in recent years to reduce nitrogen oxide (NOx) emissions. Premixed combustion combustors mostly use swirl mixing technology to achieve good mixing of fuel and oxidant, so as to meet the needs of low NOx combustion. [0003] This swirl mixing technology applies a certain tangential momentum to the airflow by setting multiple vane structures upstream of the nozzle mixing section, and the resulting turbulent disturbance enables the fuel and oxidant to achieve rapid and uniform mixing in the downstream space. It is generally believed that the greater the swirl intensity, the more uniform mixing can be achieved. However, the introduc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38
Inventor 方子文张珊珊查筱晨
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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