General Electric Company

Herbert Halila

Seetharamaiah Mannava

William D Cowie

Albert E McDaniel

James Edwin Rhoda

Stephen Joseph Ferrigno

Andrew J Lammas

William Terence Dingwell

Kurt L Hansen

James Edward Gutknecht

Michael P Swift

Douglas Paul Beneteau

Nicholas E Hollis

A turbomachine rotor blade having a dovetail-type base member, a platform carried by the base member, and an airfoil extending longitudinally from the platform in a direction opposite to that of the base member. The platform includes a forward seal wire groove and an aft seal wire groove, each of which is on opposite sides of the blade longitudinal axis and on the side of the platform facing the base member. The blade platform has a pair of recesses that each include a concave portion and an adjacent inclined ramp portion for urging a seal wire into surface-to-surface contact with the concave portions of the respective recesses. Wear of the blade platform caused by seal wire movement relative to the blade platform is significantly reduced.

Turbomachine blade-to-rotor sealing arrangement

An article and a method for improving an article that results in a reduction or elimination of damage due to fretting from contact of similar metals. The invention specifically reduces wear-related fretting between titanium alloy parts by lowering the stresses between mating parts. An aluminum bronze coating is applied to one of the parts. The aluminum bronze coating provides an improvement over prior art coatings in reducing coefficient of friction between the parts. Additionally, the cumulative stresses at the surface of the parts is reduced by a dual intensity peening treatment. This involves a first peening operation using large peening media that provides a compressive stress to the required depth. This first peening operation is followed by a second peening operation that provides additional compressive stresses closer to the dovetail surface. The combined metallurgical and mechanical improvement results in a system with less susceptibility to fretting damage and corresponding improved fatigue resistance.

Dual intensity peening and aluminum-bronze wear coating surface enhancement

A dovetail assembly for mounting blades with dovetail roots axially into disk dovetail slots around a disk periphery which is subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating. The dovetail assembly has stress risers each in the form of a transition fillet between a neck or an area of minimum width and a pressure face which is designed to be a contact surface between complementary blade dovetail roots and disk dovetail slots formed between adjacent disk posts. The region around the stress riser has deep compressive residual stresses imparted by laser shock peening and is radially adjacent the stress riser and extends inward from a laser shocked surface of the component along the transition fillet.

Laser shock peened dovetails for disks and blades

A die having a metallic block with a depression, the depression having at least one cross-sectional transition zone, at least one laser shock peened surface encompassing at least a portion of the zone, a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface. The die has been found to be useful for cold rolling blanks such when the metallic block is a cold rolling die block. The die may be adapted for forming a gas turbine engine component, such as a compressor blade, having an airfoil such that the depression corresponds to the airfoil.

Laser shock peened dies

Gas turbine engine blade with a metallic airfoil having a radially outer tip extending chordwise between a leading edge and a trailing edge and at least one laser shock peened surface extending radially along at least a portion of the tip and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.

Laser shock peened gas turbine engine blade tip

Gas turbine engine fan blade with a metallic airfoil having a leading edge, a trailing edge, and a radially outer tip, and at least one laser shock peened surface located along the leading edge with a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.

Laser shock peened gas turbine engine fan blade edges

A hollow core airfoil including a root adapted to attach the airfoil to a disk. An airfoil portion including a leading edge, a trailing edge, and a tip portion. The hollow core airfoil includes radial ribs extending from the root to the tip. Chord-wise stringers run from the leading edge to the trailing edge providing support along the chord-wise direction.

Hollow core airfoil

A plug including an axial shaft, a mating end of which is spring coupled to a mating portion of a sealing plug. The other end of the shaft includes an externally threaded portion and a flanged portion. The sealing plug also includes an externally threaded portion and a flanged portion. The spring normally mates the shaft and sealing plug together so that the members are rotationally engaged. When the spring is suitably compressed, the mating relationship is removed so that the members are rotationally disengaged. The plug is particularly useful in conveniently sealing double wall combustors such as those in gas turbine engines.

Growing community of inventors

Cincinnati, OH, United States of America

Herbert Halila