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Gas turbine combustion chamber nozzle and method for premixing fuel and air in nozzle

A gas turbine and combustion chamber technology, which is applied to combustion methods, combustion chambers, continuous combustion chambers, etc., can solve the problems of insufficient number of fuel holes on rotating blades, high flame combustion temperature, and high NOx emission, and achieves improvement of thermoacoustic oscillation. Effects of Features

Pending Publication Date: 2021-07-09
CHINA UNITED GAS TURBINE TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The disadvantage of this prior art is that, limited by mechanical processing, the number of fuel holes on the rotating blades cannot be too many, and the positions of the openings cannot be too close to the inner and outer surfaces of the premixing channel, thus causing the inner and outer surfaces of the premixing channel The fuel concentration near the wall is relatively high, the flame combustion temperature is high, and the heat release is relatively concentrated. When the gas turbine operates at the base load, the NOx emission is relatively high

Method used

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  • Gas turbine combustion chamber nozzle and method for premixing fuel and air in nozzle
  • Gas turbine combustion chamber nozzle and method for premixing fuel and air in nozzle
  • Gas turbine combustion chamber nozzle and method for premixing fuel and air in nozzle

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Embodiment 1

[0059] to combine Figure 3-4As shown, the gas turbine combustor nozzle includes a fuel delivery manifold 1 , a fuel distribution pipeline 2 , a fuel spray rod 3 and a fuel-air premixing pipe 4 . The fuel delivery main pipe 1 is in the shape of a spindle as a whole, the diameter of the fuel inlet gradually increases, and the outlet at the other end is conical, and several circular fuel distributing holes 5 are distributed on the conical shape.

[0060] In this embodiment, the fuel distributing holes 5 are uniformly distributed in the downstream outlet end of the fuel delivery main pipe 1 in a circular shape along the circumferential direction. Optionally, the fuel distributing holes 5 extend from the center of the nozzle 100 to The outside is arranged in multiple rows. After the fuel enters the system from the fuel delivery main pipe 1, it passes through the fuel distribution hole 5 on the downstream outlet of the fuel delivery main pipe 1 and then enters the fuel spray rod 3...

Embodiment 2

[0066] combine Figure 3-4 As shown, the gas turbine combustor nozzle includes a fuel delivery manifold 1 , a fuel distribution pipeline 2 , a fuel spray rod 3 and a fuel-air premixing pipe 4 . The fuel delivery main pipe 1 is in the shape of a spindle as a whole, the diameter of the fuel inlet gradually increases, and the outlet at the other end is conical, and several circular fuel distributing holes 5 are distributed on the conical shape.

[0067] In this embodiment, the fuel distributing holes 5 are uniformly distributed in the downstream outlet end of the fuel delivery main pipe 1 in a circular shape along the circumferential direction. Optionally, the fuel distributing holes 5 extend from the center of the nozzle 100 to The outside is arranged in multiple rows. After the fuel enters the system from the fuel delivery main pipe 1, it passes through the fuel distribution hole 5 on the downstream outlet of the fuel delivery main pipe 1 and then enters the fuel spray rod 3. ...

Embodiment 3

[0074] combine Figure 3-4 As shown, the gas turbine combustor nozzle includes a fuel delivery manifold 1 , a fuel distribution pipeline 2 , a fuel spray rod 3 and a fuel-air premixing pipe 4 . The fuel delivery main pipe 1 is in the shape of a spindle as a whole, the diameter of the fuel inlet gradually increases, and the outlet at the other end is conical, and several circular fuel distributing holes 5 are distributed on the conical shape.

[0075] In this embodiment, the fuel distributing holes 5 are uniformly distributed in the downstream outlet end of the fuel delivery main pipe 1 in a circular shape along the circumferential direction. Optionally, the fuel distributing holes 5 extend from the center of the nozzle 100 to The outside is arranged in multiple rows. After the fuel enters the system from the fuel delivery main pipe 1, it passes through the fuel distribution hole 5 on the downstream outlet of the fuel delivery main pipe 1 and then enters the fuel spray rod 3. ...

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Abstract

The invention provides a gas turbine combustion chamber nozzle and a method for premixing fuel and air in the nozzle. The gas turbine combustion chamber nozzle comprises a fuel conveying header pipe, fuel distribution pipelines, fuel spraying rods and fuel and air premixing pipes. The fuel conveying header pipe is provided with a plurality of fuel distribution holes, and each fuel distribution hole corresponds to at least one fuel distribution pipeline. The fuel distribution pipelines are in airflow communication with the downstream fuel spraying rods, the number of the fuel spraying rods is multiple, and each fuel spraying rod is in airflow communication with the corresponding fuel and air premixing pipe. Fuel enters from the fuel conveying header pipe, enters the fuel distribution pipelines through the fuel distribution holes and then enters the fuel and air premixing pipes through the fuel spraying rods to be mixed with air to form a mixture, and the mixture is sprayed out from the fuel and air premixing pipes. According to the gas turbine combustion chamber nozzle and the method for premixing the fuel and the air in the nozzle of the embodiment, it can be guaranteed that the whole nozzle has good fuel and air premixing uniformity.

Description

technical field [0001] The invention relates to the field of gas turbines, in particular to a gas turbine combustion chamber nozzle and a method for premixing fuel and air in the nozzle. Background technique [0002] In gas turbine DLN (Dry Low NOx, dry low nitrogen burner) combustor, the uniformity of fuel and air premixing is a key factor to control combustion NOx emissions. Since the gas turbine combustor mainly contains thermal NOx, its amount is closely related to the combustion temperature. Therefore, when the average combustion temperature is the same, the mixing uniformity of fuel and air is different, causing the local combustion temperature in different regions to deviate from the average temperature, some places are higher and some places are lower. In areas with relatively high temperatures, a large amount of thermal NOx is generated, which eventually leads to a significant increase in NOx emissions at the outlet. [0003] The gas turbine combustor nozzles in t...

Claims

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Application Information

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IPC IPC(8): F23R3/38F23R3/28
CPCF23R3/38F23R3/286
Inventor 赵光军崔玉峰王昆
Owner CHINA UNITED GAS TURBINE TECH CO LTD
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