General Electric Company

Ge Avio S.r.l.

Unison Industries, Inc.

General Electric Company Polska Sp. Z O.o.

Ge Aviation Systems Limited

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

Bugra Han Ertas

Perumallu Vukanti

Rimple Rakeshkumar Rangrej

Prateek Jalan

Andrea Piazza

Karthikeyan Sampath

Ambika Shivamurthy

Saket Singh

Weize Kang

Shai Birmaher

Daniel J Kirtley

Mohan Kannaiah Raju

Viswanadha Gupta Sakala

Shivam Mittal

Rajesh Kumar

Bruce Alan Carter

Santosh Kumar Pattnaik

Rajendra Mahadeorao Wankhade

Steven Douglas Johnson

Rahul Anil Bidkar

Vidyashankar Ramasastry Buravalla

Adam Joseph Wangler

Anand Madihalli Srinivasan

Trevor Howard Wood

Scott Alan Schimmels

Deepak Trivedi

Ajoy Patra

Abhijeet Jayshingrao Yadav

Sharad Pundlik Patil

Paul Mathew

Sripathi Mohan

Veeraraju Vanapalli

Milind Chandrakant Dhabade

Shivaram Ac

Narayanan Payyoor

Shiloh Montegomery Meyers

Subrata Nayak

Ranganatha Narasimha Chiranthan

Brandon Wayne Miller

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

Jeffrey Douglas Rambo

Steven Clayton Vise

Herbert Chidsey Roberts

Apostolos Pavlos Karafillis

Richard Alan Wesling

Duane Howard Anstead

Giridhar Jothiprasad

Tyler Frederick Hooper

Adam Tomasz Pazinski

Vishnu Vardhan Venkata Tatiparthi

Thomas Malkus

Ajith Kuttannair Kumar

Bret Dwayne Worden

Daniel Alan Niergarth

Bhaskar Nanda Mondal

Neelesh Nandkumar Sarawate

Kwanwoo Kim

Joseph Zelina

Sibtosh Pal

Rodrigo Rodriguez Erdmenger

Nathan Evan McCurdy Gibson

Brian Gene Brzek

Atanu Saha

Jonathan Russell Ratzlaff

Harsha Sanjeewa Bulathsinghalage

John Carl Glessner

Nicholas Ryan Overman

Tod Robert Steen

Eyitayo James Owoeye

Brian Christopher Kemp

Kevin Richard Graziano

Sesha Subramanian

Gurunath Gandikota

Ramana Reddy Kollam

Sheo Narain Giri

Michael Joseph Murray

Vinod Shashikant Chaudhari

Nagamohan Govinahalli Prabhakar

Jonathan Edward Coleman

Kevin Edward Hinderliter

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

Combustor for a gas turbine engine

A turbine engine is provided. The turbine engine includes: a rotor; a stator having a carrier; a seal support assembly coupled to the carrier; and a seal assembly disposed between the rotor and the stator and supported by the seal support assembly, the seal assembly defining a high pressure side and a low pressure side and including a plurality of seal segments, the plurality of seal segments having a first seal segment, the first seal segment having a seal face configured to form a fluid bearing with the rotor, a lip assembly, and a body, the lip assembly positioned on the high pressure side, the lip assembly including a seal lip having a high pressure surface defining a first angle with an axial direction and a low pressure surface defining a second angle with the axial direction, the second angle being greater than the first angle.

Seal support assembly for a turbine engine

Compressor bleed slots with variable wall structures are disclosed herein. An example apparatus disclosed herein is to be coupled to a wall of a bleed slot of a compressor of a gas turbine engine, the bleed slot defining a flow path, the apparatus comprising a member to be coupled to the wall, and a plate coupled to the member, the plate having a first geometry at a first ambient condition at a first time, the flow path having a first area when the plate has the first geometry, and a second geometry at a second ambient condition at a second time, the flow path having a second area when the plate has the second geometry, the first area greater than the second area, the first time after the second time.

Compressor bleed slots with variable wall structures

A pump system to pressurize a fluid within a closed loop transport bus is disclosed herein. The example of the pump system disclosed herein includes a pump, including an impeller, to increase kinetic energy of a fluid flowing through the impeller; an electric motor, including a rotor shaft connected to the impeller, to provide torque to the rotor shaft; a first bearing to support the rotor shaft at a first operational speed range, the first bearing coupled to an inner race; a second bearing to support the rotor shaft at a second operational speed range, the rotor shaft coupled to an outer race; and one or more sprag elements configured to: engage the inner race with the outer race at the first operational speed range; and disengage the inner race from the outer race at the second operational speed range.

Integrated bearing systems for dynamically supporting shafts in pump 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 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.

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

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Bengaluru, India

Ravindra Shankar Ganiger