A premixing nozzle for a gas turbine combustor
A gas turbine and combustion chamber technology, applied in the direction of combustion chambers, continuous combustion chambers, combustion methods, etc., can solve problems such as low speed, nozzle burnout, and flame existence, and achieve the goal of eliminating low-speed areas, reducing low-speed areas, and preventing backfire Effect
Active Publication Date: 2017-11-07
CHINA UNITED GAS TURBINE TECH CO LTD
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Problems solved by technology
Although this structure prevents the flame from entering the head area, the lower velocity in this area due to the expansion of the Venturi chamber may cause the flame to exist in this area.
Nozzles can burn out without proper cooling
Method used
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[0018] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.
[0019] figure 1 A schematic diagram of the structure principle of the premixing nozzle used in the gas turbine combustor provided by the present invention, the premixing nozzle includes a nozzle head 1, a tapered central body 2 and a mixing section 3, wherein the nozzle head 1 is provided with The peripheral gas fuel inlet 11 and the radial swirler 12; the radial swirler 12 is provided with an outer air inlet 121, and the tapered central body 2 is provided with a central gas fuel inlet 21 and a central gas fuel outlet 22; An inner layer air inlet 13 is arranged upstream of the radial swirler 12, and an annular pipe 4 coaxially arranged with the tapered central body 2 is arranged on the periphery of the tapered central body 2 in the mixing section 3. The annular pipe 4 The front end of the nozzle is connected to t...
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The invention discloses a pre-mixing nozzle used for a combustion gas turbine combustor and relates to a combustor nozzle structure with the radial vortex. According to the pre-mixing nozzle, a plurality of inner-layer air inlets are evenly formed in the upstream of a radial swirler, an annular pipe which is coaxial with a gradual contraction type center body is arranged on the periphery of the gradual contraction type center body inside a mixing section, the front end of the annular pipe is connected with the head of the nozzle, the inner wall of the annular pipe and the outer wall of the gradual contraction type center body form an annular channel, and the annular channel is communicated with the inner-layer air inlets. Air channels are introduced in the upstream of the radial swirler, and a layer of circulation channel is additionally arranged on the inner side of the mixing section, the low-speed area of the center portion due to rotating centrifugal force of the swirler can be eliminated effectively, and therefore the tempering problem of pre-mixing combustion is effectively prevented, and the service life of the pre-mixing nozzle is prolonged.
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 radial swirl. 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 introduction...
Claims
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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