Axial two-level direction inverse rotational flow nozzle of combustor of gas turbine

A technology with axial swirling and opposite directions, applied in the direction of combustion chamber, combustion method, continuous combustion chamber, etc., can solve the problems of poor mixing effect of fuel and air, pollutants affecting combustion tissue, and small airflow deflection angle, etc. Achieve the effects of improving combustion stability, improving combustion reliability, and reasonable velocity distribution

Active Publication Date: 2015-01-07
CHINA UNITED GAS TURBINE TECH CO LTD
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Problems solved by technology

However, due to the gap at the bottom of the air swirl vane, the airflow deflection angle on the inner peripheral side of the channel is small, and the swirl strength is weak, which leads to poor mixing effect of fuel and air on this side, affecting the organization of combustion and the generation of pollutants

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  • Axial two-level direction inverse rotational flow nozzle of combustor of gas turbine
  • Axial two-level direction inverse rotational flow nozzle of combustor of gas turbine
  • Axial two-level direction inverse rotational flow nozzle of combustor of gas turbine

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Embodiment Construction

[0019] The principle, structure and specific implementation of the present invention will be further described below in conjunction with the accompanying drawings.

[0020] figure 1 Schematic diagram of the structural principle of the gas turbine combustor axial two-stage direction opposite swirl nozzle provided by the present invention, the nozzle includes a central fuel channel 1, and a peripheral annular air channel 2 and a central cone arranged coaxially with the central fuel channel 6. On the central cone 6 in the peripheral axial annular air channel 2, two swirl devices with opposite swirl directions are arranged in sequence in the axial direction; the first-stage axial swirl device 4 is located in the peripheral axial annular air channel 2 The front end of the axial swirl device adopts hollow blades and communicates with the central fuel channel. There are fuel injection holes 3 on both sides of the hollow blades; the air inlet of the second-stage axial swirl device 5 i...

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Abstract

The invention discloses an axial two-level direction inverse rotational flow nozzle of combustor of gas turbine, wherein a two-level rotational flow direction inverse rotational flow nozzle is arranged in the periphery axial circular air passage along the axial direction and fixed on the centre cone; the first level rotational flow device adopts the hollow blade and is connected to a centre fuel passage, two sides of the hollow blade are opened with the fuel spraying hole; the air inlet of the second level rotational flow device is tightly pasted to the air outlet of the first level rotational flow device, the air in corner of the second level rotational flow device is the same with the air flow corner at the outlet of the first level rotational flow device, the blades of the level rotational flow devices are arranged alternately. The axial two-level direction inverse rotational flow nozzle of combustor of gas turbine can effectively increase the gas flow speed at the inner side of the air passage, strengthen the mixing rate of the fuel gas and the air, guaranteeing reasonable distribution of the outlet speed of the nozzle, evenly mix the fuel air for raising the burning stability. The impact to the outlet speed of the nozzle of the centre core attaching layer can be reduced, the downstream of the centre cone will not have the backflow region and the burning reliability can be raised.

Description

technical field [0001] The invention relates to a two-stage swirl nozzle with opposite directions in the axial direction of a combustion chamber of a gas turbine, in particular to a low-pollution combustion chamber nozzle of a gas turbine using natural gas 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 polluta...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/38
Inventor 张珊珊张正秋张龙查筱晨
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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