GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a flow sleeve structure improved in vibration-resisting performance.SOLUTION: A gas turbine combustor includes a liner 5, a transition piece 4, and a flow sleeve 7 composed of a plurality of split pieces integrated by welding a tie p...

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Bibliographische Detailangaben
Hauptverfasser:	ICHIKAWA KUNIHIRO, SEKIHARA TAKASHI
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a gas turbine combustor including a flow sleeve structure improved in vibration-resisting performance.SOLUTION: A gas turbine combustor includes a liner 5, a transition piece 4, and a flow sleeve 7 composed of a plurality of split pieces integrated by welding a tie piece 8 along their butting portions. The tie piece is continuously extended along the longitudinal direction of the butting portions of the split pieces, and composed of a first member 81 disposed to cover the butting portions, and a second member 82 formed on an end portion of the first member, being wider than the first member, and having a cutout portion 10.