General Electric Company

General Electric Deutschland Holding Gmbh

Ai Alpine US Bidco Inc.

Rodrigo Rodriguez Erdmenger

Quang Tue Nguyen Tran

Nathan Evan McCurdy Gibson

Christopher Edward Wolfe

Antonio Guijarro Valencia

Rahul Anil Bidkar

Daniel Edward Loringer

Adam Joseph Wangler

Norman Arnold Turnquist

David Raju Yamarthi

Xiaoqing Zheng

Vittorio Michelassi

Jassin Marcel Fritz

Lukas William Johnson

Ismail Hakki Sezal

Alexander Kimberley Simpson

Robbert Christiaan Pannekeet

Neelesh Nandkumar Sarawate

Steven Douglas Johnson

Deepak Trivedi

Sebastian Walter Freund

Eric John Ruggiero

Kendall Swenson

Jonathan Nagurney

Cathal Clancy

Keith Michael Parker

Maysaa Rizk

Ravindra Shankar Ganiger

Daniel Alan Niergarth

Amit Kumar Sharma

Scott Alan Schimmels

William Edward Adis

Biao Fang

Neil Xavier Blythe

Yu Du

Narendra Anand Hardikar

Giridhar Jothiprasad

David Justin Brady

Mohan Kannaiah Raju

Mehdi Milani Baladi

Prateek Jalan

Santosh Kumar Pattnaik

Michael Joseph Murray

Rudolf Konrad Selmeier

Christopher Jon Potokar

Julius John Montgomery

Prachi Anand Tappu

Matthias Carl Lang

Robert Gerard Baran

Eric Eggleston

Jose Maria Rey Villazon

Pierre Sébastien Huck

Kevin Randall McManus

Aneesh Sridhar Vadvadgi

Swaminathan Gopalakrishnan

Elisa Jubany Arribas

Nathaniel Carmello Glinbizzi

Jacek Marian Elszkowski

Rudolph Selmeier

Tran Quang Tue Nguyen

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

Apparatus, systems, and articles of manufacture are disclosed to power thermal management systems with heat of a working fluid therein. Example thermal management system include: a thermal transport bus loop fluidly coupled to at least one heat source exchanger and at least one heat sink exchanger; a turbomachine including a turbine and a compressor, the turbine and compressor rotatably interlocked via a shaft, the compressor coupled to the thermal transport bus loop, the turbine including an inlet and an outlet, the inlet connected to a first point of the thermal transport bus loop via a first flowline, the outlet connected to a second point of the thermal transport bus loop via a second flowline; and a control valve coupled to the first flowline, the control valve to adjust a mass flowrate of the heat exchange fluid in the first flowline based on a speed of the shaft.

Heat driven thermal management systems and methods for operating the same

A seal assembly for a rotary machine, such as a turbine engine, may include one or more seal segments that respectively include a seal housing defining a seal chamber and one or more fluid supply apertures that pass through the seal housing, and a seal body defining a seal face and one or more fluid conduits that pass through the seal body to the seal face. The seal chamber may receive at least a portion of the seal body, and the seal body may move within the seal chamber along a radial axis of a rotor of the rotary engine. The fluid supply apertures may fluidly communicate with the fluid conduits, and the fluid conduits may fluidly communicate with a fluid-bearing gap defined between the seal face and a rotor face of the rotor.

Seal assemblies for turbine engines and related methods

A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.

Jet engine thermal transport bus pumps are disclosed. Disclosed herein is an aircraft comprising a gas turbine engine configured to burn fuel at a fuel flow rate to generate an engine power (P), the fuel characterized by a first specific heat capacity (c) and a net heat of combustion (NHC); and a thermal management system configured to transfer heat from a working fluid to the fuel, the working fluid characterized by a second specific heat capacity (c) and a first density (ρ), the thermal management system including a pump configured to generate a pump power (P) to pressurize the working fluid, and wherein 0.008≤POW/FFR≤12, FFR is between 0.05 pounds-mass per second and 16 pounds-mass per second, and ρand cis the density and specific heat capacity of water, respectively.

Jet engine thermal transport bus pumps

A pump system for pressurizing a fluid within a closed loop thermal transport bus is disclosed herein. The example of the pump system disclosed herein includes an electric motor including a rotor shaft and a stator, wherein the rotor shaft is to generate a first torque; a pump including an impeller coupled to an impeller shaft, wherein the impeller is to increase a kinetic energy of the fluid; a driver wheel attached to the rotor shaft, wherein the driver wheel is radially connected to a follower wheel; and a co-axial magnetic coupling to connect at least one of the follower wheel to the impeller shaft or the driver wheel to the rotor shaft, wherein the co-axial magnetic coupling includes an outer hub, an inner hub, and a barrier can, the barrier can to hermetically seal a portion of the pump system from the fluid.

Radially coupled pump systems for pressurizing fluid in closed loop systems

A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.

Turbomachine and system for compressor operation

A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.

Aspirating face seal assembly for a rotary machine

An aspect of the present disclosure is directed to a seal assembly. The seal assembly includes a fluid bearing wall including a bearing face defining a fluid opening through the fluid bearing wall. The seal assembly further includes a tilt member is extended from and attached to the fluid bearing wall. The tilt member defines a fluid passage therethrough in fluid communication with the fluid opening at the bearing face of the fluid bearing wall. The seal assembly still further includes a seal body surrounding the tilt member. A cavity is defined between the tilt member and the seal body. The seal assembly further includes a spring member coupled to the seal body and the fluid bearing wall. A passage is defined between the fluid bearing wall and the seal body.

Seal assembly for a turbo machine

An aspect of the present disclosure is directed to a seal assembly for a turbo machine. The seal assembly includes a fluid bearing wall including a bearing face in which the bearing face defines a fluid opening through the fluid bearing wall. The seal assembly further includes a seal body extended circumferentially relative to a centerline axis. The seal body defines a cavity extended at least partially circumferentially through the seal body. A fluid passage is defined through the seal body in fluid communication with the fluid opening through the fluid bearing wall.

A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing.

A system includes an air source, an internal combustion engine, a first turbocharger, a second turbocharger, and a third turbocharger. The first turbocharger includes a first turbine and a first compressor, the second turbocharger includes a second turbine and a second compressor, and the third turbocharger includes a third turbine and a third compressor. The third compressor is fluidly coupled to the air source and is fluidly coupled to one of the first compressor and the second compressor. The first compressor is fluidly coupled upstream of the second compressor, and the second compressor is fluidly coupled upstream of the third turbine. The third turbine is fluidly coupled upstream of the internal combustion engine.

System for cooling engine intake flow

An aspirating face seal assembly for a turbo-machine including a rotor assembly having a first radially extending portion defining a rotor surface is disclosed. The aspirating face seal assembly includes a seal body including a second radially extending portion defining a bearing surface and having a plurality of return channels. The second radially extending portion is disposed in the turbo-machine such that the bearing surface is disposed facing the rotor surface. The aspirating face seal assembly further includes an annular ring including one or more openings. The annular ring is concentrically disposed on the second radially extending portion and between the rotor surface and the second radially extending portion and configured to rotate in an event of rub between the first radially extending portion and the annular ring. A turbo-machine including the aspirating face seal assembly and a method for operating an aspirating face seal are also disclosed.

Aspirating face seal assembly and a method of operating the same

A nozzle assembly of a turbocharger includes a nozzle and a ring-shaped body. The nozzle has flow passages extending through the nozzle and configured to direct air received from a volute housing of the turbocharger through the nozzle to turbine blades of the turbocharger. The ring-shaped body is coupled with the nozzle and is configured to rotate around the nozzle. The ring-shaped body includes blocking segments that block the flow of the air and openings between the blocking segments that permit the air to flow through the ring-shaped body. The ring-shaped body is configured to rotate relative to the nozzle to change how many of the flow passages in the nozzle are blocked by the blocking segments of the ring-shaped body.

Moveable nozzle assembly and method for a turbocharger

Growing community of inventors

Munich, Germany

Rodrigo Rodriguez Erdmenger