METHOD AND APPARATUS FOR NON-PARALLEL TURBINE DOVETAIL FACES

• Main Authors: ALBRECHT, RICHARD WILLIAM JR, LEEKE, LESLIE EUGENE, ACKERMAN, ROBERT INGRAM, MCRAE, RONALD EUGENE JR, KEITH, SEAN ROBERT
• Format: Patent
• Language: English; French
• Published: 13.01.2009
• Subjects: BLASTING; COMBINED OPERATIONS; ENGINE PLANTS IN GENERAL; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; HEATING; 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; OTHER WORKING OF METAL; PERFORMING OPERATIONS; STEAM ENGINES; TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION; TECHNICAL SUBJECTS COVERED BY FORMER USPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS; TRANSPORTING; UNIVERSAL MACHINE TOOLS; WEAPONS

A dovetail assembly (61) including non-parallel relief faces (82) that facilitates reduced pressure face brinelling in turbine engines (10). The assembly includes a plurality of rotor blades (24), each including a dovetail (44). Each dovetai l includes at least a pair of blade tangs (66, 68, 70, 72) including blade relief faces (8 2, 84). The dovetail assembly also includes a rotor disk (26) including a plurality of dovetail slots (60), each sized to receive a dovetail. Each dovetail slot is defined by at least one pair of opposing disk tangs (120, 122, 124, 126) including disk relief faces (148 , 150). The disk relief faces are non-parallel to the blade relief faces when the dovetail is mounted in the dovetail slot.