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Combustion chamber unit of gas turbine

A technology of gas turbines and combustion chambers, which is applied in the direction of gas turbine devices, combustion chambers, continuous combustion chambers, etc., and can solve limited, difficult, and difficult problems

Inactive Publication Date: 2004-10-13
MITSUBISHI HEAVY IND LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, according to the precision of the currently available processing technology, it is not always easy or quite difficult to obtain the ideal uniform precision for each nozzle, so the current state is to reduce the NO X Aspects are also limited

Method used

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  • Combustion chamber unit of gas turbine
  • Combustion chamber unit of gas turbine
  • Combustion chamber unit of gas turbine

Examples

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Embodiment Construction

[0030] Below, according to figure 1 The embodiment shown in is a more specific description of the gas turbine combustor arrangement of the present invention. It should be pointed out that although multiple fuel supply systems are proposed, only two of them are taken as representatives for illustration. exist figure 1In , reference numeral 21 denotes a fuel supply pipe, and the structure of this system is such that fuel guided through the fuel supply pipe 21 enters fuel supply systems 23 , 24 through a manifold 22 and is supplied to each combustion chamber 25 , 26 . A pressure control valve 27 and a flow control valve 28 are provided in the fuel supply pipe 21 . Also, flow control valves 29, 30 and pressure gauges 31, 32 are located in the fuel supply systems 23, 24 connected to the combustion chambers 25, 26, respectively.

[0031] Here, the structure of the entire system is made such that the flow control valves 29, 30 respectively provided in the fuel supply systems 23,...

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PUM

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Abstract

A gas turbine combustor apparatus comprises plural combustors and plural fuel supply systems realizes a combustion of a lean and uniform pre-mixture in each of the combustors to thereby enable to reduce NOx generation. Flow regulating valves are provided in fuel supply systems, respectively, that supply combustors with fuel. Pressure gauges are provided in the fuel supply systems, respectively, in front of inlets of the combustors. The flow regulating valves are controlled so that pressures measured by the pressure gauges become the same.

Description

technical field [0001] The present invention relates generally to a gas turbine combustor arrangement comprising a plurality of combustors, and more particularly to a gas turbine combustor arrangement by which a lean premixture and a homogeneous combustor can be achieved in each combustor. Combustion of premixed gas. Background technique [0002] The combustion chamber device of the gas turbine includes a plurality of combustion chambers distributed in the circumferential direction around the rotor of the gas turbine. Such as figure 2 As shown, the structure of each combustion chamber 1 is that the guide nozzle 8 is arranged in the center and a plurality of premixing nozzle devices 10 are distributed around the guide nozzle 8 . Reference numeral 11 denotes a swirl blade. While the fuel is sprayed from the dual-fuel nozzle 2 located in the premixing nozzle device 10 and mixed with air to form a premixed gas, the air imparts a swirling force through the swirling blades befo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/228F02C9/40F23R3/28F23R3/46
CPCF23N2041/20F02C7/228F23R3/46F23R3/28F23N2241/20
Inventor 青山邦明
Owner MITSUBISHI HEAVY IND LTD
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