Premixing nozzle of gas turbine combustion chamber

A gas turbine, pre-mixing technology, applied in the direction of combustion chamber, continuous combustion chamber, combustion method, etc., can solve limited problems, achieve the effect of reducing low-speed areas, preventing backfire, and eliminating low-speed areas

Active Publication Date: 2014-10-22
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Abstract
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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 pro

Method used

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  • Premixing nozzle of gas turbine combustion chamber
  • Premixing nozzle of gas turbine combustion chamber
  • Premixing nozzle of gas turbine combustion chamber

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[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

The invention discloses a premixing nozzle of a gas turbine combustion chamber and relates to a nozzle structure with axial rotational flow. According to the technical scheme, a gradually-shrinking type annular pipe is arranged between a gradually-shrinking type center body and an axial cyclone, an annular channel is formed between the gradually-shrinking type annular pipe and the gradually-shrinking type center body, an inner-layer air inlet is formed in the front end of the annular channel, and a guide vane is arranged in the annular channel. The guide vane is provided with an inner-layer fuel outlet and an inner-layer fuel channel, and the inner-layer fuel channel is communicated with a center gas fuel inlet and an outer-layer fuel channel. According to premixing nozzle, due to the feature that backfire is prone to occurring in a low-speed area, a layer of irrotational-flow or weak rotational-flow circulation channel is added on the outer side of the gradually-shrinking type center body and on the inner side of the axial cyclone. The low-speed area, caused by the rotating centrifugal force of the cyclone, of the center portion is effectively eliminated, and therefore the backfire problem of premixing combustion can be prevented, the service life of the premixing nozzle can be prolonged, and the use and maintaining cost of the gas turbine combustion chamber can be reduced.

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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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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