公开(公告)号：US20240052753A1

公开(公告)日：2024-02-15

申请号：US18081862

申请日：2022-12-15

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o.o.

Inventor： Amit Zutshi ,  Rafal Sarba ,  James Ryan Reepmeyer ,  Stefan Joseph Cafaro ,  Inenhe Mohammed Khalid ,  Daniel Edward Mollmann ,  Arjan Johannes Hegeman

IPC: F01D17/16 ,  B64D27/10

CPC classification number: F01D17/16 ,  B64D27/10

Abstract: An open rotor engine includes a core engine, a plurality of guide vanes positioned within or extending from the core engine; and a pitch change assembly operably coupled to the plurality of guide vanes. The pitch change assembly includes one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes, and a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators. The plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes. The plurality of linkage arms may have a length that differs from one another, and such length may orient a displacement or a range of motion of the respective linkage arm to an envelope of rotation about a guide vane axis that differs as between the plurality of guide vanes.

公开(公告)号：US20230378827A1

公开(公告)日：2023-11-23

申请号：US18085962

申请日：2022-12-21

Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH ,  General Electric Company Polska Sp. z o.o.

Inventor： Bugra Han Ertas ,  Joseph John Zierer, JR. ,  Vandana Prabhakar Rallabandi ,  David Allan Torrey ,  David William Crall ,  Mohamed Osama ,  Adam Tomasz Pazinski ,  Arthur William Sibbach

IPC: H02K1/20 ,  H02K5/20 ,  H02K7/18 ,  H02K21/14 ,  F02C6/00

CPC classification number: H02K1/20 ,  H02K5/203 ,  H02K7/1823 ,  H02K21/14 ,  F02C6/00

Abstract: An airgap cooling system (140) for an electric machine (100), the electric machine (100) including a rotor assembly (102) rotatably mounted within a stator assembly (120) and defining an airgap (130) therebetween, wherein the stator assembly (120) comprises a lamination stack (124). The airgap cooling system (140) includes a plurality of distribution passages (142) that extend through the lamination stack (124); a plurality of discharge passages (150) that extend between the plurality of distribution passages (142) and the airgap (130); a cooling manifold (160) defining an annular distribution plenum (164) in fluid communication with the plurality of distribution passages (142), wherein the cooling manifold (160) is configured for receiving a cooling fluid (144) and directing the cooling fluid (144) into the distribution plenum (164), through the distribution passage (142) and the discharge passage (150), and into the airgap (130).

公开(公告)号：US11735982B2

公开(公告)日：2023-08-22

申请号：US17205028

申请日：2021-03-18

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o.o. ,  General Electric Deutschland Holding GmbH

Inventor： Mohamed Osama ,  Bartlomiej Drozd ,  John Russell Yagielski

IPC: H02K11/40 ,  H02K11/21 ,  F02C6/20 ,  H02K7/18 ,  H02K11/02 ,  H02K24/00 ,  H03H1/00

CPC classification number: H02K11/40 ,  F02C6/206 ,  H02K7/1823 ,  H02K11/02 ,  H02K11/21 ,  H02K24/00 ,  H03H1/0007 ,  F05D2220/323 ,  F05D2220/76

Abstract: A hybrid-electric propulsion system is provided. In one example aspect, the hybrid-electric propulsion system includes a power converter and a propulsor. The propulsor includes a gas turbine engine having a shaft and one or more bearings supporting the shaft. The propulsor also includes an electric machine electrically coupled with the power converter. The electric machine includes a stator assembly and a rotor assembly. The rotor assembly has a rotor and a rotor connection assembly. The rotor connection assembly operatively couples the rotor with the shaft. The rotor connection assembly has an insulated joint for interrupting common mode electric current from flowing from the rotor of the electric machine to the shaft. A grounding device is included to electrically ground the shaft. The power converter includes an electromagnetic interference filter to reduce common mode voltage reaching the electric machine.

公开(公告)号：US11639669B2

公开(公告)日：2023-05-02

申请号：US17170211

申请日：2021-02-08

Applicant: General Electric Company ,  General Electric Company Polska sp. z o.o. ,  General Electric Deutschland Holding GmbH

Inventor： Bartlomiej Drozd ,  Miroslaw Sobaniec ,  Mohamed Osama ,  Darek Zatorski

IPC: F01D15/10 ,  F01D21/14 ,  F02C7/36 ,  F01D25/28 ,  F02C7/275

Abstract: A gas turbine engine includes an electrical machine positioned at least partially inward of a core airflow path, the electrical machine including an electrical rotor component and an electrical stator component, a connecting member positioned between the electrical machine and a rotary member, a disconnection device that is positionable between a disengaged position, in which the disconnection device is disengaged from the connecting member, and an engaged position, in which the disconnection device is engaged with the connecting member, and a controller including a processor, where the processor receives a signal from the electrical machine indicative of a fault, and in response to receiving the signal from the electrical machine indicative of the fault, directs the disconnection device to move from the disengaged position to the engaged position.

公开(公告)号：US11566533B2

公开(公告)日：2023-01-31

申请号：US17170229

申请日：2021-02-08

Applicant: General Electric Company ,  General Electric Company Polska sp. z o.o. ,  General Electric Deutschland Holding GmbH

Inventor： Miroslaw Czarnik ,  Adam Tomasz Pazinski ,  Bartłomiej Drozd ,  Darek Zatorski ,  Maciej Krzysztof Grunwald ,  Mohamed Osama ,  John R. Yagielski

IPC: F01D15/10 ,  F01D25/16 ,  F01D25/12 ,  F01D25/18

Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on the stator support structure. An electrical machine shaft is coupled to an end of a shaft of the propulsion engine via an intermediate shaft member extending axially between the end of the shaft and the electrical machine shaft. A bearing support frame extends from the propulsion engine, the bearing support frame defining a bearing cavity in conjunction with the electrical machine shaft. Electrical machine bearings radially extend from the bearing support frame to rotatably contact the electrical machine shaft. A rotor attached to a rotor support structure attached to the electrical machine shaft. The rotor rotates in conjunction with the electrical machine shaft to exchange energy with the shaft of the propulsion engine.

公开(公告)号：US20220372884A1

公开(公告)日：2022-11-24

申请号：US17328706

申请日：2021-05-24

Applicant: General Electric Company ,  General Electric Company Polska sp. z o.o.

Inventor： Nicholas J. Kray ,  Nicholas M. Daggett ,  Frank Worthoff ,  Damian Osowski

IPC: F01D5/32

Abstract: Preload sleeves and/or other retainers for a collet-mounted blade dovetail and/or other root are disclosed. An example turbofan for an engine includes a trunnion forming a socket for a root of a blade, a primary collet positioning the root with respect to the trunnion, and a radial preload retainer at least partially encircling the primary collet and applying a radial force with respect to the primary collet to support the primary collet positioning the root with respect to the trunnion.

公开(公告)号：US20220307380A1

公开(公告)日：2022-09-29

申请号：US17389945

申请日：2021-07-30

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o.o.

Inventor： Elzbieta Kryj-Kos ,  Piotr Jerzy Kulinski ,  Pawel Adam Lewicki ,  Ruolong Ma ,  Wendy Wenling Lin ,  Patrick Keene Clements

IPC: F01D9/02

Abstract: An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

公开(公告)号：US11454463B2

公开(公告)日：2022-09-27

申请号：US16447192

申请日：2019-06-20

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o.o.

Inventor： Pradeep Hemant Sangli ,  Vinod S. Chaudhari ,  Santosh Kumar Potnuru ,  Jeffrey Douglas Rambo ,  Michal Starzynski

IPC: F28F13/12 ,  F28F13/06 ,  B01F25/312

Abstract: The present disclosure provides fluid eductors, systems that utilize fluid eductors, and methods of entraining a suction fluid flow using a fluid eductor. Exemplary fluid eductors include a concentric eductor space or a plurality of annular eductor spaces. Exemplary methods include ejecting a volume of motive fluid out of a concentric eductor space of a fluid eductor, accelerating a peripheral region of the suction fluid flow with the motive fluid ejecting out of the first annular eductor space, and accelerating a core region of the suction fluid flow with the motive fluid ejecting out of the second annular eductor space.

公开(公告)号：US20220090507A1

公开(公告)日：2022-03-24

申请号：US17475585

申请日：2021-09-15

Applicant: General Electric Company ,  General Electric Company Polska Sp. z o. o.

Inventor： Rodrigo Rodriguez Erdmenger ,  Rudolph Selmeier ,  Mehdi Milani Baladi ,  Jacek Marian Elszkowski

IPC: F01D9/04

Abstract: 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.

公开(公告)号：US20220056846A1

公开(公告)日：2022-02-24

申请号：US17400936

申请日：2021-08-12

Applicant: General Electric Company Polska sp. z o.o ,  General Electric Company

Inventor： Adam Tomasz Pazinski ,  Miroslaw Sobaniec ,  Christopher N. Delametter

IPC: F02C7/18 ,  F02C6/00

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine. The first cooling airflow path is in communication with a second cooling airflow path located outside the enclosure that at least partially defines a second cooling airflow buffer cavity at least partially around the enclosure. A cooling duct provides pressurized air to the first cooling airflow path such that the air flows along both the first cooling airflow path and the second cooling airflow path providing the first cooling airflow buffer cavity and the second cooling airflow buffer cavity.