General Electric Company

Ge Avio S.r.l.

Unison Industries, Inc.

Ge Aviation Systems Limited

General Electric Company Polska Sp. Z O.o.

Other

Transportation IP Holdings, LLC

General Electric Deutschland Holding Gmbh

Ravindra Shankar Ganiger

Hiranya Kumar Nath

David Raju Yamarthi

Praveen Sharma

Pradeep Naik

Kudum Shinde

Shuvajyoti Ghosh

Nicholas Joseph Kray

Michael Anthony Benjamin

Narendra Anand Hardikar

Perumallu Vukanti

Prateek Jalan

Ambika Shivamurthy

Bugra Han Ertas

Karthikeyan Sampath

Rimple Rakeshkumar Rangrej

Nageswar Rao Ganji

Andrea Piazza

Daniel J Kirtley

Weize Kang

Viswanadha Gupta Sakala

Shivam Mittal

Saket Singh

Shai Birmaher

Bruce Alan Carter

Rajendra Mahadeorao Wankhade

Steven Douglas Johnson

Rahul Anil Bidkar

Anand Madihalli Srinivasan

Trevor Howard Wood

Scott Alan Schimmels

Deepak Trivedi

Rajesh Kumar

Vidyashankar Ramasastry Buravalla

Abhijeet Jayshingrao Yadav

Sharad Pundlik Patil

Veeraraju Vanapalli

Sripathi Mohan

Shivaram Ac

Kevin Lee Kirkeng

Ajoy Patra

Shiloh Montegomery Meyers

Subrata Nayak

Paul Mathew

Ranganatha Narasimha Chiranthan

Milind Chandrakant Dhabade

Adam Joseph Wangler

Richa Awasthi

Arvind Namadevan

Norman Arnold Turnquist

Nitesh Jain

Richard Ludwig Schmidt

David Allan Dranschak

Sandeep Kumar

Narayanan Payyoor

Pallavi Tripathi

Pradeep Hemant Sangli

Kishore Budumuru

Thomas Ory Moniz

Arthur William Sibbach

Steven Clayton Vise

Herbert Chidsey Roberts

Apostolos Pavlos Karafillis

Richard Alan Wesling

Duane Howard Anstead

Mark Leonard Hopper

Giridhar Jothiprasad

Vishnu Vardhan Venkata Tatiparthi

Subramani Adhiachari

Ajith Kuttannair Kumar

Brandon Wayne Miller

Bret Dwayne Worden

Jeffrey Douglas Rambo

Bhaskar Nanda Mondal

Neelesh Nandkumar Sarawate

Kwanwoo Kim

Joseph Zelina

Sibtosh Pal

Nathan Evan McCurdy Gibson

Rodrigo Rodriguez Erdmenger

Atanu Saha

Brian Gene Brzek

Jonathan Russell Ratzlaff

Harsha Sanjeewa Bulathsinghalage

Tod Robert Steen

John Carl Glessner

Nicholas Ryan Overman

Eyitayo James Owoeye

Brian Christopher Kemp

Sesha Subramanian

Gurunath Gandikota

Sheo Narain Giri

Vinod Shashikant Chaudhari

Tyler Frederick Hooper

Ramana Reddy Kollam

Nagamohan Govinahalli Prabhakar

Kevin Richard Graziano

Jonathan Edward Coleman

Michael Joseph Murray

Naleen Kumar Verma

Lubricant draining bearing assemblies are disclosed. An example apparatus includes a first race, a second race, roller bearings positioned between the first race and the second race, and a cage positioned around the roller bearings between the first race and the second race, the cage including a first radial surface, a second radial surface, and an axial surface, the first radial surface facing the first race, the second radial surface facing the second race, the axial surface facing away from the roller bearings, the cage including at least one conduit extending between the first radial surface and at least one of the second radial surface or the axial surface, the conduit defining a flow path for a fluid out of a cavity between the first race, the roller bearings, and the cage.

Lubricant draining bearing assemblies

This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include one or more paired rotors and stators and at least one interface between the rotors and the stators. The components of the stator may be axially and radially movable by vibrations and other mechanical interference. The stators comprise a sealing element, a seal housing, and a stator interface connected to the engine housing. In some examples, seal assembly includes a damping element to isolate one or more of the rotating components from vibrations mechanical interference that might misalign the rotating components from the stationary components while the turbomachine is operational. In some examples, the damping element is positioned between the seal housing and the stator interface. In other examples, the damping element is positioned between the stator interface and the engine housing.

Seal assembly for a turbomachine

An air turbine starter for starting an engine having a housing that defines an inlet, an outlet, and an air flow path extending between the inlet and the outlet. The housing includes a seal that defines at least a portion of the air flow path. A drive shaft rotatably coupled to a turbine defines a rotating axis. The turbine includes circumferentially spaced blades at least partially disposed within the air flow path. At least one bearing rotatably supports the drive shaft. A bearing support structure is located between the at least one bearing and the seal. A fluid damping assembly includes one or more conduits that fluidly couple a fluid source to a fluid reservoir.

Air turbine starter with fluid damping assembly

Oleophobic and/or oleophilic coatings to reduce heat loads on a gas turbine engine thermal management system are disclosed herein. An example method to reduce heat load in a gas turbine engine, the method including applying an oleophobic coating to an internal wall of a sump, the sump located in proximity to a heat generating element of the gas turbine engine, and applying an oleophilic coating to the heat generating element of the gas turbine engine.

Methods and apparatus for thermal management of sumps using oleophilic and oleophobic coatings

Example pump systems having dual-function annular heat exchangers are disclosed. An example pump system to pressurize a fluid within a closed loop transport bus includes a pump to move the fluid, a conduit in fluid connection with the pump, a heat exchanger positioned around at least a portion of the conduit, the heat exchanger to receive a first electrical signal transmitted in a first direction at a first time and a second electrical signal transmitted in a second direction at a second time different from the first time, the second direction opposite the first direction.

Pump systems having dual-function heat exchangers and related methods

Magnetic thrust bearing systems are disclosed. Examples disclosed herein include a thrust bearing system comprising a thrust disc protruding radially outward from a shaft, the thrust disc including a first magnet, the first magnet including a first pole at a forward side of the thrust disc and a second pole at an aft side, a first thrust pad positioned on the forward side, the first thrust pad including a second magnet adjacent to a first surface of the first thrust pad, the first surface facing the thrust disc, the second magnet including a third pole, the third and first pole having the same polarity, and a second thrust pad including a third magnet adjacent to a second surface of the second thrust pad, the second surface facing the thrust disc, the third magnet including a fourth pole, the fourth and second pole having the same polarity.

Magnetic thrust bearing systems

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.

Mounting assembly for a gearbox assembly

A windage cover for a plurality of fasteners coupling a ring gear assembly to an output shaft. The windage cover includes a clip retention member abutting an integral cover shell of the output shaft, and a foot portion configured to be inserted into a pilot groove between an integral lip and an arm portion of the output shaft. The windage cover also includes a wall portion connected to the foot portion, the wall portion being retained at one end of the wall portion by the clip retention member. The windage cover is configured to cover the plurality of fasteners.

Windage cover that covers fasteners coupling a ring gear assembly to an output shaft

A turbine engine is provided. The gas turbine engine includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments supported at least in part by the carrier, the plurality of seal segments having a first seal segment and a second seal segment, the first and second seal segments each having a seal face forming a fluid bearing with the rotor; and a seal support assembly comprising a tangential spring extension extending between the first seal segment and the second seal segment for biasing the first seal segment away from the second seal segment in the circumferential direction.

Seal support assembly for a turbine engine

A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. The rotary machine also includes a seal assembly at the rotor-stator interface. The seal assembly includes a seal rotor, a seal stator, a seal slider, and a seal defined by a rotor face of the seal rotor and a slider face of the seal slider. Further, the seal assembly includes a flexible joint connected between the slider face and a primary seal body of the seal slider. The flexible joint is configured to locally decouple movement of the slider face from the seal slider to allow the slider face to track movement of the rotor apart from the primary seal body.

Seal assembly for a rotary machine having a flexible joint

An air turbine starter (ATS) for starting an engine, having a stator including a housing having an inlet, an outlet, and a flow path extending between the inlet and the outlet and a rotor including a turbine member defining a rotating axis and having a set of blades at least partially disposed within the flow path. The ATS further including a bearing support structure disposed between the rotor and the stator comprising a first bearing support having a first stiffness (K) and a second bearing support having a second stiffness (K).

Air turbine starter with bearing support structure

A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

Differential gearbox assembly for a turbine engine

A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.

Method of controlling rotor thrust loading in a turbine engine

Oil lubricated supercritical fluid pumps with oil separators are disclosed herein. An example pump system to pressurize a fluid within a closed loop thermal transport bus disclosed herein includes a pump housing, a duct fluidly coupled to the pump housing, a first portion of the duct to include a mixture of an oil and the supercritical fluid, a second portion of the duct to include the supercritical fluid, and a separator positioned in a third portion of the duct between the first portion of the duct and the second portion of the duct, the separator to separate the oil in the mixture from the supercritical fluid.

Oil lubricated fluid pumps with oil separators

Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction, the first annular substrate defining a cavity at a radially inward surface of the first annular substrate, a second annular substrate positioned at least partially within the cavity of the first annular substrate, and a tension belt extending circumferentially around a periphery of the second annular substrate.

Variable flowpath casings for blade tip clearance control

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Bengaluru, India

Ravindra Shankar Ganiger