DAMPER CONFIGURED TURBINE BLADE

• Main Authors: GARAY, GREGORY TERRENCE, BAUER, RANDALL CHARLES, WEAVER, MATTHEW MARK, BAILEY, JAMES ROBERT, BUSBEY, BRUCE CLARK
• Format: Patent
• Language: English; French
• Published: 07.03.2017
• Subjects: BLASTING; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION; ENGINE PLANTS IN GENERAL; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; 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; TECHNICAL SUBJECTS COVERED BY FORMER USPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ARTCOLLECTIONS [XRACs] AND DIGESTS; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE; WEAPONS

A turbine rotor blade (10) includes a hollow airfoil (12) joined to a platform (14) and dovetail (16). A main flow channel (6) extends longitudinally in span through the blade (10) and is bound chordally by opposite partitions (34) transversely bridging opposite sidewalls (20,22) of the airfoil (12). A damper rib (44) and transversely opposite damper pad (48) are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil (12) and chordally positioned intermediate to the partitions (34) to provide unobstructed forward and aft portions of the flow channel (6) for channeling a coolant (32) therethrough. The damper ribs (44) and pads (48) are configured to receive a wire damper (42) through the channel (6) to locally dampen vibration while minimizing obstruction of the coolant flow (32) therethrough.