gas turbine
A technology for gas turbines and turbines, which is applied in gas turbine installations, combustion chambers, mechanical equipment, etc., and can solve the problems of non-replacement and difficulty of intermediate parts or transition parts.
Active Publication Date: 2021-02-26
MAN ENERGY SOLUTIONS SA
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- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
In gas turbines known from practice, this has caused difficulties, that is to say such that intermediate or transition pieces cannot be replaced without extensive assembly work on the rest of the gas turbine
Method used
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Embodiment Construction
[0052] The invention relates to a gas turbine. figure 1 An axial section through the gas turbine 10 is shown in the region of the compressor 11 , the turbine 12 and the combustor 13 having at least one combustion chamber connected between the compressor 11 and the turbine 12 . A stator-side housing 14 and a rotor-side shaft 15 with a plurality of compressor stages are shown in the compressor 11 . A stator-side housing 16 with a plurality of turbine stages and a rotor-side shaft 17 are shown in the turbine 12 . A rotor-side shaft 15 of the compressor 11 and a rotor-side shaft 17 of the turbine 12 are coupled to one another.
[0053] A burner housing 18 is shown in the combustor 13 , which is connected between the stator-side housing 14 of the compressor 11 and the stator-side housing 16 of the turbine 12 . The burner housing 18 preferably has a plurality of recesses 19 , wherein each recess 19 of the receptacle is used to accommodate at least one flame tube 20 of a correspond...
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A gas turbine with: a compressor in which air can be compressed; a combustor having a combustion chamber in which the compressed air can be delivered to the combustor and where it is Combustion of fuel by heating the compressed air; turbine, in which the heated air can be decompressed; where the heated air can be fed from the combustion chamber of the burner to the turbine via an intermediate piece , the intermediate piece is fixed at the guide vane carrier of the turbine with the downstream end; wherein the intermediate piece has a fixing element with a threaded hole with an internal thread at the downstream end; wherein the fixing element of the intermediate piece extends into the turbine In the recess of the guide vane carrier; wherein the guide vane carrier has an unthreaded passage groove; wherein the fixing element of the intermediate part is passed through the passage hole with the unthreaded passage hole and the passage hole passing through the holding element, the passage groove of the guide vane carrier The retaining element and the fixing bolt of the threaded hole of the fixing element are assembled at the vane carrier.
Description
technical field [0001] The invention relates to a gas turbine. Background technique [0002] The basic structure of a gas turbine, for example an industrial gas turbine, is basically known to those skilled in the art mentioned here. Thus, the gas turbine has a compressor, a burner with at least one combustion chamber, and a turbine as important components. In the compressor, an air flow is compressed, wherein the air flow compressed in the compressor can be fed to one or each combustion chamber of the gas turbine. In one or each combustor of the gas turbine, fuel is combusted in the presence of compressed air, thereby heating the air. From one or each combustor, heated air is delivered to the turbine of the gas turbine, where the heated air is decompressed in the turbine. The operating power of such a gas turbine then results from the difference between the power delivered by the turbine and the power consumed by the compressor. This difference is produced by the introdu...
Claims
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IPC IPC(8): F01D9/02F23R3/44
CPCF02C3/00F01D9/023F23R3/60F23R3/44F01D9/02F01D25/243F05D2260/31
Inventor E.阿申布鲁克J.E.马萨尔梅M.布拉斯维希
Owner MAN ENERGY SOLUTIONS SA