General Electric Company

Sang Yeng Park

Christopher Charles Glynn

John Frederick Ackerman

William Randolph Stowell

Robert Alan Johnson

Roger C Walker

Peter W Mueller

Joseph T Stevenson

Daniel Edward Wines

Mitchell Jay Headley

Frederick Martin Miller

Poul D Pedersen

Julius Bathori

Josef Panovsky

Christopher Karl Hubley

Clifford C May

Fatih Sari

Alkim Deniz Senalp

Khalil Qader

Michael Edward McCann

Soon Jai Khang

Dan Ivkovich

Michael Edward Mccann

An interlocking shroud assembly for a turbine engine includes at least two shroud elements, each having confronting radial ends that define a split interface with axial fore, aft, and circumferential portions.

Shroud for a turbine engine

A curvic seal for use in a gas turbine engine is provided. The curvic seal includes a split ring including a first slit extending therethrough, and a biasing ring coupled to the split ring and extending along a radially inner side thereof. The biasing ring is configured to bias against the split ring and restrict airflow through the first slit.

Curvic seal for use in a gas turbine engine and method of assembling a gas turbine engine

A gas turbine engine blade having a dovetail with an enhanced surface for durability is disclosed. The blade includes an airfoil section and a dovetail section disposed opposite the airfoil section. The dovetail section has an outer surface, at least a portion of which has residual compressive stresses resulting from a plurality of peening operations. The dovetail section also includes a copper-nickel-indium wear coating layer disposed over the outer surface having residual compressive stresses and a lubricant coating layer disposed over the copper-nickel-indium wear coating layer, wherein the lubricant coating layer is lead-free.

Dovetail surface enhancement for durability

A bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct. The torque tube connects a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan duct. The bearing assembly includes a bearing having a spherical external engagement surface and a housing having a flange and an annular interior surface having an inner edge and an outer edge. The interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane lying between the inner and outer edges. The contact plane is tilted with respect to the flange at an angle greater than five degrees.

Torque tube bearing assembly

An engine, according to an exemplary embodiment of the invention, comprises a compressor which compresses inlet air; a combustor in which a mixture of fuel and air is combusted; a turbine which is driven by gases from the combustor; and a dielectric coating applied to a surface of at least one of: the compressor and the turbine, the dielectric coating having a dielectric constant of at least 3.0 and a loss tangent of at most 0.1, wherein the dielectric coating reduces the magnitude of an electrostatic force which attracts particles flowing through the engine to the surface of the engine. In operation, only a thin layer of particles typically accumulates on the dielectric coating. While the dielectric coating reduces the magnitude of the electric field which attracts particles, the repulsive force produced by the accumulated particles repels additional particles of the same charge. By reducing particle deposits, exemplary embodiments of the invention can reduce degradation in engine performance and provide significant cost savings through avoidance of maintenance.

Engine having resistance to particle deposits

One form of a retention system includes a pair of aft segments of 180.degree. in length disposed in annular grooves about a compressor spool, the segments having radial projections against which the aft end faces of the base portions of rotor blades abut. The blade base portions are shaped and are received in complementary-shaped slots of the spool. The forward retention system includes a plurality of arcuate segments approximately 30.degree. in length disposed in grooves adjacent the forward end faces of the blades. With the exception of the final pair of blades, the blade base portions thereof are located in the axial complementary slots in pairs, with each forward arcuate segment, except the final segment, being disposed in the groove at a circumferentially spaced location and displaced circumferentially to abut the forward end faces. The final arcuate segment is radially reduced and disposed in the remaining portion of the groove to lie flush with the spool. The base portions of the final blades are axially inserted over the final segments and the latter is displaced radially outwardly and pinned to abut the forward end faces of the final blade base portions. In another form, tabs project forwardly or rearwardly from the base portions of the blades. The tabs have holes in registry with corresponding holes in the blade slot for receiving pins thereby preventing axial movement of the blades relative to the spool.

Retention system for the blades of a rotary machine

The present invention provides a phase independent damper and damper assembly capable of damping rotor blade vibrations in the axial, circumferential, and radial directions. One embodiment, particularly useful in an aircraft gas turbine engine compressor rotor, provides a damper and damper assembly including a generally axially extending blade damper operable to fictionally engage a generally axially extending circumferentially facing surface of a disk and axially extending angled surface under the platform of the blade. The invention provides an additional advantage of allowing simple and easy modification of existing engines to incorporate the damper of the present invention.

Blade damper

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West Chester, OH, United States of America

Sang Yeng Park