Gas Turbine Combustor Premixed Fuel Nozzles

A technology for fuel nozzles and gas turbines, used in combustion chambers, continuous combustion chambers, combustion methods, etc., can solve problems such as backfire, and achieve the effects of reducing emissions, simple and reasonable structure, and good versatility

Active Publication Date: 2018-05-25
BEIJING HUAQING GAS TURBINE & INTEGRATED GASIFICATION COMBINED CYCLE ENG TECH
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a gas turbine combustor premixed fuel nozzle to overcome the flashback phenomenon in the prior art due to the existence of stable vortices attached to the solid wall and staying in the mixing channel for a long time behind the nozzle problems, thus ensuring that the nozzle head is not burned, and also ensuring the safety and reliability of the gas turbine

Method used

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  • Gas Turbine Combustor Premixed Fuel Nozzles
  • Gas Turbine Combustor Premixed Fuel Nozzles

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Embodiment Construction

[0022] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but should not be used to limit the scope of the present invention.

[0023] Such as figure 1 , 2 As shown, the gas turbine combustor premixed fuel nozzle of this embodiment includes:

[0024] The central vertebral body 3, the central vertebral body 3 is an axial hollow structure, and the hollow cavity of the central vertebral body 3 is the central fuel channel 1;

[0025] The diversion casing 4, the diversion casing 4 is set on the periphery of the central vertebral body 3 and arranged coaxially with the central vertebral body 3, and the annular air passage 2 is formed between the diversion casing 4 and the central vertebral body 3;

[0026] Radial fuel pipe 5, the radial fuel pipe 5 is radially arranged between the central cone 3 and the guide housing 4;

[00...

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Abstract

The invention relates to the technical field of gas turbines, and specifically discloses a premixed fuel nozzle for a combustion chamber of a gas turbine, comprising: a central cone, the central cone is a hollow structure, and the hollow cavity of the central cone is a central fuel passage; The flow shell is set on the periphery of the central cone and arranged coaxially with the central cone, and there is an annular air passage between the flow guide shell and the central cone; the radial fuel pipe is arranged radially on the central cone Between the body and the diversion shell; the auxiliary cone, the auxiliary cone is arranged on the radial fuel pipe and arranged parallel to the central cone, the auxiliary cone is a hollow structure, and the hollow cavity of the auxiliary The central fuel channel is connected, and fuel injection holes are arranged on the auxiliary cone. The invention can reasonably control the flow of fuel and air to produce a better mixing effect and form a stable flame downstream of the nozzle.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a premixed fuel nozzle for a combustion chamber of a gas turbine. Background technique [0002] The traditional gas turbine combustor adopts diffusion combustion technology, and its pollutant emissions, especially nitrogen oxide emissions, are relatively high. The combustor using premixed combustion technology is used for gas turbine power generation, which is one of the clean energy technologies. It can effectively reduce the emission of pollutants while meeting the power generation load requirements. Among them, the design of the gas turbine combustor nozzle is very important for organizing combustion and reducing Pollutant emissions are particularly important. [0003] At present, in the prior art of pre-mixing nozzles, stable vortexes attached to the solid wall and staying in the mixing channel for a long time tend to exist behind the nozzles, resulting in the occurrenc...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/28
Inventor 张珊珊刘小龙查筱晨
Owner BEIJING HUAQING GAS TURBINE & INTEGRATED GASIFICATION COMBINED CYCLE ENG TECH
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