Gas turbine combustion chamber and transition piece

A gas turbine combustion chamber 2 is provided, including a flow sleeve 7 structure with an improved anti-vibration performance. A gas turbine combustion chamber 2 of the present invention includes a liner 5, a transition piece 4, and a flow sleeve 7 including a plurality of segments and integrated...

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Bibliographische Detailangaben
Hauptverfasser:	Ichikawa, Kunihiro, Sekihara, Masaru
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES ENGINE PLANTS IN GENERAL GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine combustion chamber 2 is provided, including a flow sleeve 7 structure with an improved anti-vibration performance. A gas turbine combustion chamber 2 of the present invention includes a liner 5, a transition piece 4, and a flow sleeve 7 including a plurality of segments and integrated by welding a tie piece 8 along joint portions of the segments. The tie piece 8 includes a first member 81 and a second member 82, the first member 81 continuously extending along a longitudinal direction of the joint portions of the segments and being arranged to cover the joint portions, and the second member 82 being formed at an end portion of the first member 81, having a width wider than the first member 81, and including a recess 10.