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A gas turbine combustor dual fuel nozzle

A gas turbine and combustion chamber technology, which is applied to combustion chambers, continuous combustion chambers, combustion methods, etc., can solve problems such as less than ideal and increase the difficulty of air bleed in the center of the nozzle, and achieve stable combustion effect, good outlet temperature distribution, and good mixing. effect of effect

Active Publication Date: 2017-10-03
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0004] However, the fuel distribution effect of the centrifugal fuel nozzle is not ideal compared with the pre-film nozzle under certain load conditions. Achieving proper droplet size and distribution before combustion increases the difficulty of bleed air into the center of the nozzle

Method used

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  • A gas turbine combustor dual fuel nozzle
  • A gas turbine combustor dual fuel nozzle

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Embodiment Construction

[0014] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.

[0015] figure 1 Schematic diagram of the structure principle of a gas turbine combustor dual-fuel nozzle provided by the present invention, the nozzle includes a central cone 1, an inner layer air flow channel 5 and an outer layer air flow channel 6; the center cone 1 is internally arranged with an annular fuel gas channel 3 And the central fuel passage 4, the inner airflow passage 5 and the outer airflow passage 6 are respectively arranged with an inner air swirl device 7 and an outer air swirl device 8.

[0016] The inner and outer air swirl devices are located at the same axial position, and the front end of each blade is provided with a radial fuel gas hollow channel 2 and a radial fuel gas hollow channel 9 . The radial fuel gas hollow channel 2 communicates with the annular fuel gas channel 3, and the radial...

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Abstract

A gas turbine combustion chamber double-fuel nozzle comprises a central cone, an inner airflow channel and an outer airflow channel. An inner air rotational flow device and an outer air rotational flow device are arranged in the inner airflow channel and the outer airflow channel respectively, a radial fuel gas hollow channel and a radial fuel oil hollow channel are formed in the front end of each blade of the air rotational flow device, oil supply holes are formed in two sides of each radial fuel oil hollow channel, an axial seam groove is formed in the outer air rotational flow device, and the front end of the axial seam groove is communicated with the radial fuel oil hollow channels. The radial position of the seam groove, the height of the seam groove, the diameters and inclined angles of oil supply holes are adjusted, so that two fuels form different fuel spraying modes in the inner rotational flow device and the outer rotational flow device, requirements to the fuels under different loads are met, better mixing effects are achieved, excellent outlet temperature distribution is formed, and stable combustion effects are realized.

Description

technical field [0001] The invention relates to a dual-fuel nozzle of a combustion chamber of a gas turbine, in particular to a nozzle of a combustion chamber of a gas turbine using dual fuel. Background technique [0002] In my country's current energy structure, thermal power generation using traditional coal-fired technology occupies the vast majority of the share. However, this traditional power generation technology has disadvantages such as low power generation efficiency, high pollutant emissions (especially NOx emissions), and high consumption of fresh water resources. As one of the clean energy technologies, the gas turbine power generation technology fueled by natural gas 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 combustion chamber of a gas turbine, ...

Claims

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Application Information

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IPC IPC(8): F23R3/38
Inventor 张龙张珊珊查筱晨刘小龙
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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