Air inlet structure for fuel nozzle of gas turbine

A technology for fuel nozzles and gas turbines, applied in combustion chambers, combustion methods, combustion equipment, etc., can solve the problems of head burnout, nozzle prone to tempering, tempering, etc., and achieve the effect of improving reliability and preventing tempering

Active Publication Date: 2015-03-25
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In prior art premixed fuel nozzles, flashback is prone to occur behind the nozzle, requiring a light blow of air to protect the rear of the nozzle
However, the flow rate of light blowing air is often different in different environments and climates. A low flow rate of light blowing air will lead to backfire, resulting in the head being burned, which seriously affects the safety and reliability of the gas turbine.

Method used

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  • Air inlet structure for fuel nozzle of gas turbine
  • Air inlet structure for fuel nozzle of gas turbine
  • Air inlet structure for fuel nozzle of gas turbine

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Embodiment Construction

[0021] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0022] In the description of the present invention, it should be noted that unless otherwise specified and limited, the term "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; directly or indirectly through an intermediary. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

[0023] combine figure 1 and image 3 As shown, an air intake structure of a gas turbine fuel nozzle provided by an embodiment of the present invention, the fuel nozzle includes an inner pipe 4 and an outer pipe 5, th...

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Abstract

The invention relates to the technical field of gas turbines, and provides an air inlet structure for a fuel nozzle of a gas turbine. The fuel nozzle comprises a center air channel and a fuel cavity which are communicated with each other, and the center air channel is used for connecting the air into the fuel cavity. A nozzle hanging flange is arranged at one end of the center air channel, and the nozzle hanging flange is provided with air inlet channels used for connecting the air into the center air channel. The nozzle hanging flange is movably sleeved with an adjusting sleeve, and the adjusting sleeve is used for limiting the sizes of openings of the air inlet channels through axial movement. By axially adjusting the adjusting sleeve, the flow of the air entering the center air channel can be adjusted, hence, it is guaranteed that fuel and air have a good pre-mixing effect, tempering can be prevented from happening to a nozzle outlet, and the reliability of the nozzle is improved; in addition, stepless speed change of the gas turbine can be achieved through the adjusting sleeve.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to an air intake structure of a gas turbine fuel nozzle. Background technique [0002] The traditional gas turbine combustor adopts diffusion combustion technology. Due to the local high temperature in the combustion chamber, the pollutant emissions, especially the nitrogen oxide emissions, are relatively high. The combustor using premixed combustion for gas turbine power generation technology is one of the clean energy technologies, which can effectively reduce pollutant emissions while meeting the power generation load requirements. Among them, the design of the gas turbine combustor nozzle is particularly important for organizing combustion and reducing pollutant emissions. [0003] In the prior art of premixed fuel nozzles, the rear of the nozzle is prone to flashback, so a light blow of air is required to protect the rear of the nozzle. However, the flow rate of light bl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/04F23R3/26
Inventor 查筱晨张珊珊刘小龙张龙
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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