Gas Turbine Combuster

a technology of combustor and gas turbine, which is applied in the direction of machines/engines, transportation and packaging, lighting and heating apparatus, etc., can solve the problems of periodic fluctuation of the pressure in the combustion chamber, and the oscillation of the combustion chamber

Pending Publication Date: 2021-04-22
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text explains that the "technical effects" of the text are meant to be clarified by the descriptions of examples. This means that the text is explaining a problem that needs to be solved or a structure that needs to be improved. The goal of the text is to provide a way to explain the problem or structure in a clear and concise manner. The text does not provide additional information about the technical effects of the example.

Problems solved by technology

However, in a certain case, the mode fails to stabilize the combustion state, leading to combustion oscillation that periodically fluctuates the pressure in the combustion chamber.

Method used

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  • Gas Turbine Combuster
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Examples

Experimental program
Comparison scheme
Effect test

first example

[0022]An explanation will be made conceptually with respect to the gas turbine power generation facility provided with a gas turbine combustor 3 (hereinafter referred to as a combustor) according to a first example.

[0023]FIG. 1 conceptually illustrates the gas turbine power generation facility provided with the combustor 3 according to the first example.

[0024]The gas turbine power generation facility (gas turbine power plant) provided with the combustor 3 according to the first example includes a turbine 2, a compressor 1 connected to the turbine 2 for generating compressed air 5 for combustion, a plurality of gas turbine combustors 3, and a generator 4 connected to the turbine 2 for generating power in association with driving of the turbine 2. FIG. 1 shows one unit of the combustor 3 for convenience of explanation.

[0025]The compressed air 5 discharged from the compressor 1 is supplied to the combustor 3 via a compressed air passage 6. In a combustion chamber 8 formed inside a comb...

second example

[0052]A main part of the combustor 3 according to a second example will be briefly described.

[0053]FIG. 3 is a schematic partially enlarged sectional view of the main part of the combustor 3 according to the second example.

[0054]The combustor 3 according to the second example is different from the combustor 3 according to the first example in the use of a flow sleeve 50 instead of the supports 41 and the vane 40.

[0055]The flow sleeve 50 is an annular member disposed in the annular passage 13 in substantially parallel to the combustion liner 7 in the radial direction of the annular passage 13 for narrowing its cross section area through which the compressed air 5 flows.

[0056]The flow sleeve 50 is disposed to expand toward the outer circumferential side downstream in the flow direction of the compressed air 5 flowing through the annular passage 13 (around the outer circumferential side of the flame stabilizer 35). The flow sleeve 50 is fixed to the inner circumferential side of the co...

third example

[0074]A main part of the combustor 3 according to a third example will be briefly described.

[0075]FIG. 4 is a schematic partially enlarged sectional view of the main part of the combustor 3 according to the third example.

[0076]The combustor 3 according to the third examples is different from the combustor 3 according to the first example in the state where the supports 41 and the vane 40 are disposed in the circumferential direction.

[0077]The combustor 3 according to the first example is configured to set the uniform gap g1 between the outer circumference (outer circumferential surface) of the combustion liner 7 and the inner circumference (inner circumferential surface) of the vane 40 in the circumferential direction. Meanwhile, the combustor 3 according to the third example is configured to set the non-uniform gap between the outer circumference (outer circumferential surface) of the combustion liner 7 and the inner circumference (circumferential surface) of the vane 40 in the cir...

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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

CLAIM OF PRIORITY[0001]The present application claims priority from Japanese Patent application serial no. 2019-190106, filed on Oct. 17, 2019, the content of which is hereby incorporated by reference into this application.BACKGROUND OF THE INVENTION[0002]The present invention relates to a gas turbine combustor.[0003]Gas turbine combustors of some type use liquefied natural gas as fuel. In this case, from an aspect of global environment conservation, a premixed combustion mode for combustion of air-fuel premixture is employed to suppress emission of nitrogen oxides (NOx) as a cause of air pollution.[0004]In the premixed combustion mode, the air-fuel premixture may suppress generation of a locally high-temperature combustion region in burning. It is therefore possible to suppress generation of nitrogen oxides from the high-temperature combustion region.[0005]Generally, the premixed combustion mode succeeds in suppressing quantity of generated nitrogen oxides. However, in a certain ca...

Claims

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Application Information

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IPC IPC(8): F23R3/06F23R3/10F23R3/28F02K1/34
CPCF23R3/06F23R3/10F23D2210/00F02K1/34F23R3/28F23R2900/00014F23R3/16F23R3/005F23R3/286F23R3/44F23R3/002F23R2900/03043
Inventor YOSHIDA, SHOHEIHIRATA, YOSHITAKAHAYASHI, AKINORIDODO, SATOSHITAKAHASHI, HIROKAZU
Owner MITSUBISHI HEAVY IND LTD
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