Method for a part load co reduction operation for a sequential gas turbine
A gas turbine, local technology, applied in combustion methods, continuous combustion chambers, gas turbine installations, etc., can solve problems such as increased CO production in the incinerator, increase in the minimum fuel flow of the second combustor, inhomogeneity of the annular combustor, etc. To achieve the effect of reducing the original cost and eliminating the possibility
Active Publication Date: 2015-02-25
ANSALDO ENERGIA SWITZERLAND AG
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Problems solved by technology
The minimum load at which the second burner operates and the minimum fuel flow into the second burner is thus significantly increased
At high loads this leads to the desired inhomogeneity in the annular burner
However, at low loads, this inhomogeneity resulted in a disproportionate increase in CO production for at least one limiting incinerator
Method used
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[0101] Figures 1 to 3 A gas turbine with continuous combustion for carrying out the method according to the invention is shown. It includes a compressor, a first combustor can, a second combustor can and a turbine. Typically, it comprises a generator, not shown here, coupled to the shaft of the gas turbine at the cold end of the gas turbine, ie at the compressor.
[0102] figure 1 A normal gas turbine using continuous combustion is shown in barrel frame, adding valves for modulating dilution air;
[0103] figure 2 A normal gas turbine using continuous combustion is shown in barrel frame, adding valves for modulating dilution air;
[0104] image 3 shows a normal gas turbine using continuous combustion in a barrel / annular frame, adding valves for modulating the dilution air;
[0105] exist figure 1 and figure 2 On top of the engine architecture shown in , the concept is expected to be in image 3Work on the engine frame shown in . So basically the transition betwee...
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The invention concerns a method for a part load CO reduction operation and a low-CO emissions operation of a gas turbine with sequential combustion. The gas turbine essentially comprises at least one compressor, a first combustor which is connected down-stream to the compressor, and the hot gases of the first combustor are admitted at least to an intermediate turbine or directly or indirectly to a second combustor. The hot gases of the second combustor are admitted to a further turbine or directly or indirectly to an energy recovery. At least one combustor runs under a caloric combustion path having a can-architecture (4, 15), and wherein the air ratio (lambda) of the combustion at least of the second combustor (15') is kept below a maximum air ratio (lambdamax).
Description
technical field [0001] The invention relates to a method for operating a gas turbine with continuous combustion. Furthermore, the invention relates to a gas turbine for implementing a method for operating a gas turbine with continuous combustion and low CO emissions. Background technique [0002] To protect the environment, CO emissions from gas turbine engines need to be reduced. Such emissions are known to have insufficient time in the combustion chamber to ensure CO to CO 2 Oxidation and / or localized quenching of this oxidation due to contact with a cold zone in the burner. Since the incineration temperature is smaller under partial load conditions CO, the CO to CO 2 Oxidation of becomes slower, so CO emissions generally tend to increase in these states. [0003] The reduction in CO emissions can then be invested in reducing the gas turbine load at the shutdown point of the gas turbine. This is due to the reduction of CO 2 Environmental impact is reduced due to lowe...
Claims
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IPC IPC(8): F02C6/00F02C7/228F02C9/34F23C6/04F02C3/14
CPCF02C7/228Y02E20/16F02C6/003F23R2900/03341F02C3/14F02C9/34Y02E20/14F23C6/042F02C9/28F05D2220/74
Inventor M.杜伊辛A.埃罗格鲁
Owner ANSALDO ENERGIA SWITZERLAND AG