公开(公告)号：US20240229673A9

公开(公告)日：2024-07-11

申请号：US18048609

申请日：2022-10-21

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Timothy Unton ,  Andrew Eifert ,  Michael Moser

IPC: F01D17/16 ,  F04D29/56

CPC classification number: F01D17/162 ,  F04D29/563 ,  F05D2240/12

Abstract: A vane assembly includes a casing, vanes, and an actuator assembly. The vanes are arranged within the casing and are rotatably coupled to the casing for rotation relative thereto and configured to rotate about their pitch axes. The actuator assembly is arranged radially outward of the casing and includes an annular ring surrounding the casing and coupled to the vanes, a magnet arranged on the ring, and a stator spaced apart from the magnet. The ring is configured to rotate the vanes about their pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and ring about the central axis. The stator is configured to create a magnetic field which causes annular movement of the ring via interaction with the magnet.

公开(公告)号：US12025059B1

公开(公告)日：2024-07-02

申请号：US18088994

申请日：2022-12-27

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Robert W. Heeter ,  Daniel E. Molnar, Jr. ,  Kathryn A. Sontag ,  Michael G. Meyer

IPC: F02C9/20 ,  F02C3/04 ,  F02C6/00

CPC classification number: F02C9/20 ,  F02C3/04 ,  F02C6/00 ,  F05D2220/32 ,  F05D2220/70 ,  F05D2270/05 ,  F05D2270/101

Abstract: A gas turbine engine comprises a primary fan and an engine core. The primary fan is mounted for rotation about an axis of the gas turbine engine to provide thrust. The engine core is coupled to the primary fan and configured to drive the primary fan about the axis to cause the fan to push air to provide thrust for the gas turbine engine.

公开(公告)号：US12018621B1

公开(公告)日：2024-06-25

申请号：US18234657

申请日：2023-08-16

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Robert W. Heeter ,  Daniel E. Molnar, Jr. ,  Michael S. Krautheim

IPC: F02C9/22 ,  F01D17/14 ,  F02K3/06 ,  F04D29/54

CPC classification number: F02C9/22 ,  F01D17/141 ,  F02K3/06 ,  F04D29/542 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/14

Abstract: A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a channel that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the channel and spaced apart circumferentially about the axis.

公开(公告)号：US12018580B1

公开(公告)日：2024-06-25

申请号：US18231565

申请日：2023-08-08

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Ryan C. Humes

IPC: F01D5/02 ,  F01D5/30

CPC classification number: F01D5/027 ,  F01D5/3038 ,  F05D2230/60 ,  F05D2240/59

Abstract: A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight assembly is configured to balance a weight distribution of the rotor assembly.

公开(公告)号：US11988151B1

公开(公告)日：2024-05-21

申请号：US18179651

申请日：2023-03-07

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Alan W. Smith ,  Sara Karaffa

IPC: F02C7/32 ,  F01D15/10 ,  F02C7/268 ,  H02K1/18 ,  H02K7/18

CPC classification number: F02C7/32 ,  F01D15/10 ,  F02C7/268 ,  H02K1/185 ,  H02K7/1823 ,  F05D2220/323 ,  F05D2220/76 ,  F05D2230/60 ,  F05D2260/85

Abstract: Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.

公开(公告)号：US11970985B1

公开(公告)日：2024-04-30

申请号：US18234654

申请日：2023-08-16

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Robert W. Heeter ,  Daniel E. Molnar, Jr. ,  Jonathan M. Rivers ,  Michael S. Krautheim

IPC: F01D17/14 ,  F02C9/22 ,  F04D29/52 ,  F04D29/54 ,  F04D29/68

CPC classification number: F02C9/22 ,  F01D17/141 ,  F04D29/526 ,  F04D29/542 ,  F04D29/68

Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

公开(公告)号：US20240124150A1

公开(公告)日：2024-04-18

申请号：US18393008

申请日：2023-12-21

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Douglas J. Snyder

IPC: B64D33/10 ,  B64D37/34 ,  F02C7/12 ,  F02C7/224 ,  F02K7/10

CPC classification number: B64D33/10 ,  B64D37/34 ,  F02C7/12 ,  F02C7/224 ,  F02K7/10 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/303 ,  F05D2270/3062 ,  F05D2270/44 ,  F05D2270/56

Abstract: A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

公开(公告)号：US11946414B2

公开(公告)日：2024-04-02

申请号：US17553700

申请日：2021-12-16

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： Robert W. Heeter ,  Christopher D. Hall ,  Daniel E. Molnar, Jr.

IPC: F02C7/045 ,  F02K1/82 ,  G10K11/168 ,  G10K11/172

CPC classification number: F02C7/045 ,  F02K1/827 ,  G10K11/168 ,  G10K11/172 ,  F05D2220/323 ,  F05D2260/963 ,  F05D2300/121 ,  F05D2300/603 ,  F05D2300/612

Abstract: An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

公开(公告)号：US20240056007A1

公开(公告)日：2024-02-15

申请号：US17819527

申请日：2022-08-12

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Peter Schenk ,  Erik A. Munevar ,  Rigoberto J. Rodriguez

IPC: H02P9/08 ,  F02C7/268

CPC classification number: H02P9/08 ,  F02C7/268 ,  H02P2101/25

Abstract: An example system includes a power electronics system; a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft; and an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system, wherein the power electronics system is configured to deliver alternating current (AC) electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from an AC electrical bus of the aircraft.

公开(公告)号：US11873765B1

公开(公告)日：2024-01-16

申请号：US18095220

申请日：2023-01-10

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Ryan C. Humes

IPC: F02C7/32 ,  F02C6/14

CPC classification number: F02C7/32 ,  F02C6/14 ,  F05D2260/4031 ,  F05D2260/43

Abstract: A gas turbine engine system includes a gas turbine engine, an accessory gearbox, and a flywheel powered barring engine system. The gas turbine engine includes a rotor and a turbine. The accessory gearbox is connected with the rotor. The flywheel powered barring engine system is connected with the accessory gearbox and configured to rotate the rotor after shut down of the gas turbine engine.