General Electric Company

Barry Lynn Allmon

Jan Christopher Schilling

Daniel Edward Mollmann

Duane Howard Anstead

William Clarke Brooks

Lee Alan Blanton

Bala Corattiyil

Courtney James Tudor

Edward Atwood Rainous

Stephen Anthony Wilton

Vicky Showalter Budinger

Morris Green Penn

Jeffre Gerry Loewe

Kevin B Tongeman

Christopher Charles Glynn

Randy M Vondrell

Gert Johannes Van Der Merwe

Ethan Patrick O'Connor

Kenneth Lee Fisher

Anant Pal Singh

Anthony John Durchholz

Jerry Lynn Cabe

Michael Joseph Gambone

Thomas Matthew Doerflein

Richard Leon Riffle

Anthony Durchholz

Randy Marinus Vondrell

A gearbox assembly includes a first gear coupled to a first shaft, a second gear coupled to a second shaft, and a plurality of planet gears that mesh with the first gear and the second gear. The first shaft includes a first shaft stiff portion and a first shaft flexible portion that includes a greater flexibility than a flexibility of the first shaft stiff portion such that the first gear moves in a radial direction. The second shaft includes a second shaft stiff portion and a second shaft flexible portion that includes a greater flexibility than a flexibility of the second shaft stiff portion such that the second gear moves in the radial direction. The first gear and the second gear move to distribute loads substantially equally on the plurality of planet gears.

Gearbox assembly

A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.

Ice shed reduction for leading edge structures

A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface.

A bearing assembly for a gas turbine engine rotor includes, in an exemplary, an inner race, an outer race assembly, and a rolling element. The outer race assembly includes a body, a plurality of first springs attached to the body, and a plurality of second springs. Each first spring is radially aligned with a corresponding second spring forming a spring pair. The outer race assembly also includes a plurality of connecting members. Each connecting member extends between and connects a first end of the first spring and a first end of the second spring of said spring pair. The outer race assembly further includes a flange with each second spring attached to the flange.

Apparatus for centering rotor assembly bearings

An apparatus for scavenging lubricating oil comprises an integrated slinger/runner rotatable with the turbine engine rotor discourages oil seepage out of an oil sump of a forward bearing for a gas turbine engine during all operating conditions of the gas turbine engine from idle to take-off speeds and during static non-operation. The apparatus includes a runner comprising an axially forward section and a frusto-conical aft section, and a slinger joined coaxially integrally to the aft frusto-conical aft section. The apparatus includes a means for blocking flow of oil from the frusto-conical aft section toward the axially forward section.

Apparatus for scavenging lubricating oil

A method facilitates the assembly of a stator assembly for a turbine engine. The method includes providing a cantilevered shell including a first end and a second end, and coupling a second member within the turbine engine. The method also includes coupling the shell to a frame such that the shell extends circumferentially around at least a portion of the second member such that a non-uniform circumferential radial gap is defined radially between the second member and the shell using methods other than directing machining of an inner surface of the shell, and wherein the non-uniform circumferential radial clearance gap becomes substantially uniform during operation of the engine.

Methods for optimizing turbine engine shell radial clearances

A bearing assembly for a gas turbine engine rotor includes a paired race, a bearing, a mounting joint, and a plurality of mechanical fuses. The paired race includes an outer race and an inner race. The bearing is between the inner and outer races, and is configured to support the rotor on a support frame. The mounting joint includes a joint inner race and a joint outer race. At least one of the joint inner race and the joint outer race includes a spherical surface. The mounting joint is configured to reduce dynamic loads to the gas turbine engine structure and static bending to the rotor. The plurality of mechanical fuses extend through at least one of the joint inner race and the joint outer race.

Method and apparatus for supporting rotor assemblies during unbalances

A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.

Methods and apparatus for bearing outer race axial retention

A rotor assembly for a gas turbine engine includes a bearing assembly that reduces dynamic loads to a support frame and static bending to the rotor assembly during periods of rotor unbalance. The rotor assembly includes a rotor shaft coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race, a rolling element, and a mounting race. The mounting race includes a spherical face and is secured to the bearing assembly with a retainer that plastically fails at a pre-determined moment load.

A rotor assembly for a gas turbine engine including a bearing centering sub-assembly that facilitates reduces an effect of radial forces transmitted to a bearing assembly is described. The bearing assembly supports a rotor shaft with a rolling element positioned radially inward from an outer race. The bearing centering sub-assembly is coupled to the outer race and includes a plurality of first springs and a plurality of second springs extending circumferentially in rows. Each first springs is coupled between a second spring and the outer race such that each first spring is radially aligned with respect to each second spring.

Method and apparatus for centering rotor assembly damper bearings

An air-oil separating arrangement in a gas turbine engine having a sump with a rotatable annular wall structure includes an annular section of the sump wall structure having a plurality of circumferentially spaced air metering orifices defined therein, and an air-oil separator having a circular plate attached to the annular section of the sump wall structure and rotatable therewith. The circular plate has a pair of opposite faces and a plurality of separator fins attached to and extending from one face of the plate. The separator fins are circumferentially spaced from one another and extend radially from the center of the plate and define spaces therebetween which are in flow communication with the orifices through the annular section of the sump wall structure. The engine also includes a center vent passage aligned with the center of the separator plate such that when oil particle-laden pressurized air flows from the sump through the metering orifices and radially inwardly through the radial spaces between the separator fins into the center vent passage, the oil particles carried by the air will be impacted by the fins and centrifugally ejected in an outward radial direction back outwardly through the metering orifices and thereby separated from the air flow through the separator and returned to the sump.

Growing community of inventors

Maineville, OH, United States of America

Barry Lynn Allmon