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Method of controlling the fuel distribution among different stages of a gas turbine combustion chamber

A fuel distribution, gas turbine technology, applied in the direction of control combustion, combustion method, combustion chamber, etc., can solve the problems of flame extension, pulsation, etc.

Pending Publication Date: 2016-08-24
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] During these abnormal transient operations, the delay between the measurement of the load or a parameter indicative of the load and the implementation of the fuel distribution may result in the implementation of a fuel distribution that does not correspond to the current load, where operation is close to lean blowout with flame extension and / or the risk of pulsating

Method used

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  • Method of controlling the fuel distribution among different stages of a gas turbine combustion chamber
  • Method of controlling the fuel distribution among different stages of a gas turbine combustion chamber
  • Method of controlling the fuel distribution among different stages of a gas turbine combustion chamber

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Embodiment Construction

[0033] Referring to the drawings, these show a gas turbine 1 with a compressor 2 for compressing an oxidant such as air, a combustor 3 for combusting the fuel with the compressed oxidant to produce hot gas, and for expanding the hot gas and collecting Turbine 4 of mechanical work.

[0034] The combustion chamber may be of any type, in the following reference is made to a combustion chamber arranged for carrying out premixed combustion.

[0035] The combustion chamber 3 has one or more burners 6 connected to burners 7 . The incinerator 6 has a substantially conical shape with a notch 8 extending axially on the conical surface for the supply of an oxidant 9 into the incinerator 6 .

[0036] The burner 6 is also provided with nozzles for fuel supply.

[0037] The first nozzle 10 defines a first fuel supply stage and is provided at the end portion of the burner 6 in order to supply fuel into the burner 7 for combustion; the fuel supplied via the first stage undergoes diffusion c...

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Abstract

A method of controlling the fuel distribution among different stages of a gas turbine combustion chamber (3) is disclosed. The combustion chamber (3) has at least two stages for fuel supply, and the fuel distribution between the stages is determined according to the load or one or more parameters indicative of the load. In reply to a fast load change being faster than a load change during a regular transient operation, the fuel distribution is determined according to an adjusted load or one or more parameters indicative of an adjusted load.

Description

technical field [0001] The present invention relates to a method of controlling fuel distribution between different stages of a gas turbine combustor. Background technique [0002] Gas turbines are known to include a compressor for compressing an oxidant, such as air, a combustor where the fuel and compressed air are combusted to produce hot gases, and a turbine where the hot gases are expanded to concentrate mechanical work. [0003] The combustor may have a staged fuel supply. Combustion chambers with staged fuel supply have a number of fuel nozzles that can be independently fueled in order to adjust the fuel distribution within the combustion chamber by adjusting the fuel injected through different stages of nozzles. [0004] During operation, fuel distribution may be adjusted based on one or more parameters of load or performance load in order to maintain gas turbine operation within an optimal or acceptable operating condition within a larger operating load window (e.g...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F23R3/28
CPCF23R3/28F05D2270/331F23N1/002F23R3/346F02C9/26F02C9/28F02C9/32F05D2220/32F05D2240/35F23R3/10F23R3/286
Inventor T.弗雷拉-普罗维达基斯R.L.R.史密斯T.米尤维斯森T.马奇奥内
Owner ANSALDO ENERGIA IP UK LTD
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