General Electric Company

General Electric Renovables Espana, S.l.

James Edward Cencula

Donald L Bellia

Hahn M Spofford

Priyangu Chunilal Patel

Thomas P Joseph

Raed Zuhair Hasan

Lawrence Keith Taliaferro, Jr

Steven Sebastian Burdgick

Thomas G Wakeman

George Albert Goller

Gregory Allan Crum

Edward Lee McGrath

Wei Jun Zheng

Rong Li

Nicholas Francis Martin

John R Hess

Michael Harvey Schneider

Jonathan Paul Signore

Gregg Hunt Wilson

John Alan Eastman

Gary D Mercer

Michael Garry

Souvik Porel

Frederick W Tegarden

Tingyu Zhang

Farong Zhu

Kevin M Vandevoorde

Robert A McLeod

Laurence Seelen

Yash Dayashankar Jaiswal

Edward Lee Mcgrath

Subramani Adhiachari

The present disclosure is directed to a system for monitoring wear on a gearbox of a wind turbine. A controller of the system is configured to determine a torque exerted on a rotor shaft of the wind turbine or a generator shaft of the wind turbine based on measurement signals received from a first sensor of the system. The controller is also configured to determine an accumulated wear value for the gearbox based on the torque.

System and method for monitoring wear on a gearbox of a wind turbine

A repair method for a gearbox assembly for a wind turbine is disclosed. The gearbox includes a gearbox housing having an upwind end and a downwind end, a gear assembly configured within the gearbox housing, at least one shaft configured with the gear assembly and extending from the gearbox housing to a generator of the wind turbine, and a sleeve assembly configured with the gearbox housing. Further, the sleeve assembly is removable so as to provide additional space in the gearbox housing during at least one of disassembly or assembly of the gearbox assembly such that the various components can be easily repaired and/or replaced.

Repair method for a gearbox assembly of a wind turbine

An integral ring gear and torque arm for a wind turbine gearbox and method of manufacturing same includes forming the ring gear and the associated gear housing as a single part using the same material, e.g., using a casting process. Further, the ring gear defines an inner circumferential surface having a plurality of gear teeth. Thus, the method also includes applying a coating material to the gear teeth of the ring gear via an additive manufacturing process, such as cold spraying, so as to increase a hardness of gear teeth.

Integral ring gear and torque arm for a wind turbine gearbox

A compressor radial bleed manifold and compressor case assembly includes a compressor case having one or more bleed flow exit passages therein; and a discrete bleed manifold mounted on the compressor case and having one or more inlet passages extending radially between a manifold plenum and the one or more exit passages in the mounting boss for bleeding compressor air into the manifold plenum.

Bolt-on radial bleed manifold

A turbine casing is provided in two casing halves joined one to the other along a horizontal splitline having flanges with spaced boltholes. A circumferentially extending rib is provided about each casing half at a location just forward of the turbine buckets to minimize or eliminate distortion caused by internal pressure and meridional roll of the casing. One or more axially extending ribs is provided on each casing half. The axial ribs have a radial stiffness which substantially matches the stiffness and thermal response of the flanges.

Casing distortion control for rotating machinery

An aircraft engine thrust mount includes a pair of spaced apart thrust links pivotally joined at one end to an engine first frame and at opposite ends to a lever. A platform is fixedly joined to an aircraft pylon and includes first and second spaced apart clevises and a center clevis therebetween. The center clevis is pivotally joined to a center of the lever for carrying thrust force from the first frame through both thrust links and to the platform and pylon during normal operation. A pair of pins pivotally join the thrust links to the lever and extend through apertures in the platform first and second clevises to define predetermined gaps therebetween for allowing the lever to rotate relative to the platform center clevis up to a predetermined angular rotation. In a failure mode of operation the pins contact the platform first and second clevises for transmitting thereto either tension or compression thrust loads for providing an alternate failsafe loadpath. In a preferred embodiment, the platform further includes an aft mount joined to an engine second frame spaced aft of the engine first frame.

Aircraft engine thrust mount

An aircraft engine mounting assembly using a clevis type joint to connect a link is provided with a mounting pin assembly disposed in an aperture of the link having inexpensive and easily replaceable concentric inner and outer non-rotational bushings surrounding a conventional pin and corresponding oppositely disposed sets of inner flat contact surfaces on the outer surface of inner bushing and outer flat contact surfaces on the inner surface of the outer bushing which provide reduced contact stresses between the pin and the aperture as compared to conventional assemblies. The contact surfaces are in general sliding engagement in the longitudinal direction and are provided with clearances between the inner and outer bushings in the longitudinal and transverse directions to allow for thermal growth of the engine.

Aircraft engine pin mount

An aircraft engine mount includes a frame fixedly joined in a gas turbine engine and a platform fixedly joined to an aircraft wing or tail pylon. A first beam is pivotally joined to the frame and the platform at first and second joints, respectively. The first beam is additionally joined to the platform at a third joint which allows longitudinal movement between the first beam and the platform at the third joint while preventing rotation of the first beam. A second beam is spaced from the first beam and is pivotally joined to the frame and platform at fourth and fifth joints, respectively, and is additionally joined to the platform at a sixth joint for allowing limited rotation of the second beam during normal operation while preventing rotation of the second beam upon a failure of the first beam to carry load.

Aircraft engine mount

Growing community of inventors

Greer, SC, United States of America

James Edward Cencula