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Gas Turbine Combuster

A gas turbine and burner technology, which is applied in the combustion chamber, combustion method, combustion equipment, etc., can solve the problems of unstable combustion state, periodic fluctuation of combustion chamber pressure, combustion vibration, etc.

Active Publication Date: 2021-04-20
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Generally speaking, the premixed combustion method can suppress the generation of nitrogen oxides, but sometimes the combustion state is unstable, and sometimes combustion vibrations in which the pressure of the combustion chamber fluctuates periodically occur.

Method used

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  • Gas Turbine Combuster
  • Gas Turbine Combuster
  • Gas Turbine Combuster

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] First, a gas turbine power plant having the gas turbine combustor (hereinafter referred to as a combustor) 3 described in Embodiment 1 will be conceptually described.

[0031] figure 1 It is an explanatory diagram conceptually explaining a gas turbine power plant having the combustor 3 described in the first embodiment.

[0032] A gas turbine power generation facility (gas turbine power plant) having the combustor 3 described in Embodiment 1 has a turbine 2, a compressor 1 connected to the turbine 2 to generate compressed air 5 for combustion, a plurality of gas turbine combustors 3, and a turbine 2 A generator 4 that is connected to generate electricity as the turbine 2 is driven. In addition, in figure 1 In , for convenience of description, one burner 3 is described.

[0033] The compressed air 5 discharged from the compressor 1 flows through the compressed air passage 6 and is supplied to the combustor 3 . Compressed air 5 and fuel are combusted in a combustion c...

Embodiment 2

[0061] Next, main parts of the burner 3 described in Example 2 will be schematically described.

[0062] image 3 It is a partial enlarged cross-sectional view schematically explaining the main part of the burner 3 described in the second embodiment.

[0063] The burner 3 described in the second embodiment is different from the burner 3 described in the first embodiment in that a flow sleeve 50 is provided instead of the bracket 41 and the blade 40 .

[0064] The airflow sleeve 50 is an annular member provided in the annular flow path 13 . The airflow sleeve 50 is provided substantially parallel to the inner tube 7 in the radial direction of the annular flow path 13 so as to narrow the annular flow path 13 through which the compressed air 5 flows.

[0065] Furthermore, the airflow sleeve 50 is provided so as to expand toward the outer peripheral side on the downstream side (near the outer peripheral side of the flame holder 35 ) in the flow direction of the compressed air 5 ...

Embodiment 3

[0084] Next, main parts of the burner 3 described in Example 3 will be schematically described.

[0085] Figure 4 It is a partial enlarged cross-sectional view schematically explaining the main part of the burner 3 described in the third embodiment.

[0086] The combustor 3 described in Example 3 differs from the combustor 3 described in Example 1 in the arrangement state of the bracket 41 and the vane 40 in the circumferential direction.

[0087] In the combustor 3 described in Embodiment 1, the gap g1 between the outer peripheral side (outer peripheral surface) of the inner tube 7 and the inner peripheral side (inner peripheral surface) of the blade 40 is constant in the circumferential direction. On the other hand, in the combustor 3 described in Embodiment 3, the gap between the outer peripheral side (outer peripheral surface) of the inner cylinder 7 and the inner peripheral side (inner peripheral surface) of the blade 40 is not constant in the circumferential direction....

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PUM

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Abstract

A gas turbine combustor with a relatively simple structure is configured to attenuate pressure fluctuation owing to combustion oscillation while securing mechanical reliability. The gas turbine combustor includes a combustion liner that forms a combustion chamber for generating combustion gas, a combustion casing disposed at an outer circumferential side of the combustion liner, and a burner for supplying air flowing between the combustion liner and the combustion casing, and fuel to be supplied from a fuel supply system to the combustion chamber. The combustor further includes a vane disposed at the outer circumferential side of the combustion liner, a plurality of supports disposed at an inner side of the combustion casing for fixing the vane, and a pressure dynamics damping hole formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.

Description

technical field [0001] The invention relates to a gas turbine combustor. Background technique [0002] Gas turbine combustors sometimes use liquefied natural gas as fuel. Furthermore, in this case, from the viewpoint of environmental protection, in order to suppress the emission of nitrogen oxides (NOx), which is one of the causes of air pollution, premixed combustion in which fuel and air are premixed and then combusted may be used. Way. [0003] Because the premixed combustion method premixes fuel and air, it can suppress the occurrence of local high-temperature combustion regions during combustion, and can suppress the generation of nitrogen oxides caused by high-temperature combustion regions. [0004] In general, the premixed combustion method can suppress the amount of nitrogen oxides produced, but sometimes the combustion state is unstable, and sometimes combustion vibrations in which the pressure of the combustion chamber fluctuates periodically occur. Therefore, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28F23R3/42
CPCF23R3/06F23R2900/00014F23R3/10F23R3/16F23R3/005F23R3/286F23R3/28F23R3/44F23R3/002F23R2900/03043
Inventor 吉田正平平田义隆林明典百百聪高桥宏和
Owner MITSUBISHI HEAVY IND LTD