GAS TURBINE INCLUDING BELLY BAND SEAL ANTI-ROTATION DEVICE

A sealing band located in opposing seal band receiving slots of adjacent turbine disks to seal an annular gap therebetween. An anti-rotation body including a base portion is located between edges of the sealing band within the annular gap, and a pin portion extends axially from the base portion for...

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Bibliographische Detailangaben
Hauptverfasser:	UHRAN, PAUL A, GURAO, MANISH S, LIGHT, KEVIN M, LAGROW, MATTHEW J
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS 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 MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	A sealing band located in opposing seal band receiving slots of adjacent turbine disks to seal an annular gap therebetween. An anti-rotation body including a base portion is located between edges of the sealing band within the annular gap, and a pin portion extends axially from the base portion for engagement with a cut-out portion of at least one of the disks. A pair of spaced projections extend from the base portion and into through openings in the sealing band at a location within the annular gap. The projections define an attachment structure attaching the anti-rotation body to the sealing band. L'invention concerne une bande d'étanchéité placée dans des fentes de réception de bande d'étanchéité opposées de disques de turbine adjacents pour sceller un espace annulaire entre ceux-ci. Un corps anti-rotation comprenant une partie base est disposé entre des bords de la bande d'étanchéité à l'intérieur de l'espace annulaire, et une partie goupille s'étend axialement à partir de la partie base pour s'accoupler à une partie découpe d'au moins un des disques. Une paire de saillies espacées s'étendent à partir de la partie base et dans des ouvertures traversantes dans la bande d'étanchéité à un emplacement à l'intérieur de l'espace annulaire. Les saillies définissent une structure de fixation fixant le corps anti-rotation à la bande d'étanchéité.