General Electric Company

Unison Industries, Inc.

Ge Aviation Systems Limited

General Electric Company Polska Sp. Z O.o.

David Raju Yamarthi

Ravindra Shankar Ganiger

Adam Joseph Wangler

David Allan Dranschak

Santosh Kumar Pattnaik

Eliel Fresco Rodriguez

Mohan Kannaiah Raju

Parmeet Singh Chhabra

Amit Arvind Kurvinkop

Shiloh Montegomery Meyers

Narendra Anand Hardikar

Anand Shankar Tanavde

Prachi Anand Tappu

Brian Christopher Kemp

Prateek Jalan

Steven Douglas Johnson

Subrata Nayak

Paul Mathew

David Justin Brady

Marc David Zinger

Grant Robert Portune

Deepak Trivedi

Rahul Anil Bidkar

Rodrigo Rodriguez Erdmenger

Brian Gene Brzek

Sandeep Kumar

Vidyashankar Ramasastry Buravalla

Sharad Pundlik Patil

Balamurugan Sridharan

Pallavi Tripathi

William Hunter Boardman, Iv

Jasraj Asdev

Rajendra Vishwanath Pawar

Steven Ryan Kerley

Roberto Karpik

Bajarang Agrawal

Nagashiresha G

Shishir Paresh Shah

Chandrashekhar Kandukuri

Nilesh Vilas Varote

Murugesan Periasamy

Jeffrey Douglas Rambo

William Edward Adis

Rajesh Kumar

David Robert Schumacher

Michael Joseph Murray

Ismail Hakki Sezal

Vishnu Vardhan Venkata Tatiparthi

David Norwood Dorsey

Nagendra Baddam

Vasanth Kumar Balaramudu

Sagar Paramashivaiah

Tajinder Singh

Christopher Michael Dahlberg

Navin Soni

Maysaa Rizk

Himanshu Gupta

Brandon Wayne Miller

Daniel Alan Niergarth

Norman Arnold Turnquist

Anand Madihalli Srinivasan

Hiranya Kumar Nath

Nitesh Jain

Narayanan Payyoor

Richard Nils Dawson

Richard Alan Wesling

Kudum Shinde

John Carl Glessner

Gary Willard Bryant, Jr

Tod Robert Steen

Mark Leonard Hopper

Ramana Reddy Kollam

Sheo Narain Giri

Adam Tomasz Pazinski

Kevin Edward Hinderliter

Nageswar Rao Ganji

Mandyam Rangayan Sridhar

Deepak Ghiya

Amit Goyal

Anirban Chatterjee

Narendra Dev Mahadevaiah

Shalini Thimmegowda

Ankita Sinha

Mamatha Ramakrishnaiah

Lakshminarayana Kanakamedala

Douglas Lorrimer Armstrong

Pratish Patil

Mohammad Khaja Mohiddin Shaik

Srinivasan Swaminathan

Sanjeev Sai Kumar Manepalli

Venkata Subramanya Sarma Devarakonda

Souvik Porel

Shiloh Montegomery Emerson Meyers

Gautam Suresh Naik

Rachamadugu Sivaprasad

Dhiraj Khushal Thakare

Guru Venkata Dattu Jonnalagadda

Nuthi Srinivas

Saurya Ranjan Ray

Nathaniel Philip Marshall

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

Dual compression-expansion pumps and related methods are disclosed. An example fluid pump includes a shaft, a motor coupled to the shaft, the motor to drive a rotation of the shaft, a compressor coupled to a first end of the shaft, a turbine coupled to a second end of the shaft opposite the first end, and a housing including a first inlet, a second inlet, a third inlet, a first outlet, and a second outlet, the first outlet fluidly coupled to the second inlet, the second outlet fluidly coupled to the third inlet.

Dual compression-expansion pumps and related methods

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

Impeller bearings for pumps are disclosed. An example fluid pump includes a motor, a shaft coupled to a rotor of the motor, an impeller coupled to the shaft forward of the motor, the impeller including blades to pump a fluid, a first radial bearing positioned around the shaft aft of the motor, a second radial bearing positioned around the impeller, and guide vanes extending radially from the second radial bearing upstream of the blades of the impeller.

Impeller bearings for pumps

Layered barrier cans and methods of producing the same are disclosed herein. An example shroud disclosed herein includes an inner shell including a first non-metallic material, an outer shell including the first non-metallic material or a second non-metallic material, and a metal core shell positioned between the inner shell and the outer shell.

Layered barrier cans for pumps and methods of producing the same

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 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.

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 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.

A method and system used to control a rotational speed or a torque of an output drive shaft. The output drive shaft being coupled to a turbine engine. The turbine engine including an engine core and an engine starter assembly. The engine starter assembly including an air turbine starter, an output drive shaft and an electric motor.

Turbine engine including an engine starter assembly

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

Example thrust bearing apparatus includes: a thrust disk extending radially from the shaft, the thrust disk having a first side and a second side opposite the first side; a bearing housing surrounding the thrust disk and the shaft, the bearing housing having a first wall facing the first side of the thrust disk and a second wall facing the second side of the thrust disk; a first thrust pad coupled to the first wall of the bearing housing, the first thrust pad including a first plurality of serrations circumferentially arranged in a first pattern along the first thrust pad; and a second thrust pad coupled to the first side of the thrust disk, the second thrust pad including a second plurality of serrations circumferentially arranged in a second pattern along the second thrust pad.

Dual thrust bearing systems and methods for operating the same

Growing community of inventors

Bengaluru, India

David Raju Yamarthi