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

Narendra Anand Hardikar

Shuvajyoti Ghosh

Nicholas Joseph Kray

Michael Anthony Benjamin

Perumallu Vukanti

Prateek Jalan

Bugra Han Ertas

Karthikeyan Sampath

Rimple Rakeshkumar Rangrej

Ambika Shivamurthy

Andrea Piazza

Weize Kang

Saket Singh

Daniel J Kirtley

Viswanadha Gupta Sakala

Shivam Mittal

Shai Birmaher

Mohan Kannaiah Raju

Bruce Alan Carter

Rajendra Mahadeorao Wankhade

Steven Douglas Johnson

Rahul Anil Bidkar

Rajesh Kumar

Santosh Kumar Pattnaik

Anand Madihalli Srinivasan

Trevor Howard Wood

Scott Alan Schimmels

Deepak Trivedi

Ajoy Patra

Vidyashankar Ramasastry Buravalla

Abhijeet Jayshingrao Yadav

Sharad Pundlik Patil

Paul Mathew

Veeraraju Vanapalli

Sripathi Mohan

Adam Joseph Wangler

Milind Chandrakant Dhabade

Shivaram Ac

Narayanan Payyoor

Shiloh Montegomery Meyers

Subrata Nayak

Ranganatha Narasimha Chiranthan

Richa Awasthi

Arthur William Sibbach

Norman Arnold Turnquist

Nitesh Jain

Richard Ludwig Schmidt

David Allan Dranschak

Sandeep Kumar

Mark Leonard Hopper

Pallavi Tripathi

Pradeep Hemant Sangli

Kishore Budumuru

Thomas Ory Moniz

Steven Clayton Vise

Herbert Chidsey Roberts

Apostolos Pavlos Karafillis

Richard Alan Wesling

Duane Howard Anstead

Giridhar Jothiprasad

Tyler Frederick Hooper

Vishnu Vardhan Venkata Tatiparthi

Thomas Malkus

Adam Tomasz Pazinski

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

Brian Gene Brzek

Atanu Saha

Jonathan Russell Ratzlaff

Harsha Sanjeewa Bulathsinghalage

Nicholas Ryan Overman

John Carl Glessner

Tod Robert Steen

Eyitayo James Owoeye

Brian Christopher Kemp

Kevin Richard Graziano

Sesha Subramanian

Gurunath Gandikota

Vinod Shashikant Chaudhari

Sheo Narain Giri

Ramana Reddy Kollam

Nagamohan Govinahalli Prabhakar

Michael Joseph Murray

Jonathan Edward Coleman

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 gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.

Mounting assembly for a gearbox assembly

A bearing having a bearing surface with a groove, the bearing positioned adjacent to a shaft, the groove facing the shaft, and a negative thermal expansion (NTE) material positioned in the groove, the NTE material at least partially filling the groove.

Bearings with grooves and methods of producing the same

A pump system for pressurizing a fluid within a closed loop supercritical transport bus is disclosed herein. The examples of the pump system disclosed herein include an impeller coupled to an impeller shaft; an axial flux electric motor including rotors and a stator; a rotor shaft connected to the rotors, wherein the rotor shaft is coupled to the impeller shaft; a seal to prevent the fluid from contacting the axial flux electric motor; a first housing to frame the impeller shaft; and a second housing to frame the axial flux electric motor, wherein the second housing is separate from the first housing.

Axial flux motor driven pump systems for pressurizing fluid in closed loop systems

A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

Bearing support assembly

A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.

Combustor deflector assembly

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 includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

A turbine engine is provided. The gas turbine engine defines a radial direction, and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment having a seal face forming a fluid bearing with the rotor; and a seal support assembly comprising a torsional spring extension extending from the carrier, from the seal segment, or both, to bias the seal segment along the radial direction.

Seal support assembly for a turbine engine

A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly including a magnet assembly having a magnet coupled to the carrier or the seal segment for biasing the first seal segment along the radial direction.

A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.

Shaft for a turbomachine

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

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Bengaluru, India

Ravindra Shankar Ganiger