公开(公告)号：US11878812B2

公开(公告)日：2024-01-23

申请号：US17702754

申请日：2022-03-23

Applicant: Rolls-Royce Corporation

Inventor： Peter M. Schenk ,  Rigoberto Rodriguez ,  David Locascio

IPC: B64D41/00 ,  H02K1/2783 ,  H02K9/22 ,  H02K7/00 ,  F01D15/10 ,  H02K7/08

CPC classification number: B64D41/007 ,  H02K1/2783 ,  H02K7/006 ,  H02K7/08 ,  H02K9/22 ,  F01D15/10

Abstract: The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

公开(公告)号：US11851770B2

公开(公告)日：2023-12-26

申请号：US17002203

申请日：2020-08-25

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

Inventor： Matthew R. Gold ,  Michael Cybulsky ,  Stephanie Gong ,  Li Li

IPC: C23C28/04 ,  C23C4/11 ,  C23C4/134 ,  F01D5/28 ,  C23C28/00 ,  C04B41/87 ,  C04B41/50 ,  C04B41/00 ,  C23C4/073 ,  B32B18/00 ,  C23C24/08 ,  C04B111/00 ,  B32B15/16

CPC classification number: C23C28/042 ,  B32B18/00 ,  C04B41/009 ,  C04B41/5042 ,  C04B41/87 ,  C23C4/073 ,  C23C4/11 ,  C23C4/134 ,  C23C24/08 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  F01D5/288 ,  B32B15/16 ,  C04B2111/0025 ,  C04B2111/00577 ,  C04B2235/3224 ,  C04B2235/5436 ,  C04B2235/5445 ,  C04B2235/76 ,  C04B2237/343 ,  C04B2237/348 ,  C04B2237/586 ,  C04B2237/588 ,  C04B2237/704 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2300/15 ,  F05D2300/2112 ,  F05D2300/2118 ,  C04B41/5042 ,  C04B41/4527 ,  C04B41/5045 ,  C04B41/526

Abstract: An article that includes a substrate; a first layer including yttria and zirconia or hafnia, where the first layer has a columnar microstructure and includes predominately the zirconia or hafnia; a second layer on the first layer, the second layer including zirconia or hafnia, ytterbia, samaria, and at least one of lutetia, scandia, ceria, neodymia, europia, and gadolinia, where the second layer includes predominately zirconia or hafnia, and where the second layer has a columnar microstructure; and a third layer on the second layer, the third layer including zirconia or hafnia, ytterbia, samaria, and a rare earth oxide including at least one of lutetia, scandia, ceria, neodymia, europia, and gadolinia, where the third layer has a dense microstructure and has a lower porosity than the second layer.

公开(公告)号：US11835064B1

公开(公告)日：2023-12-05

申请号：US18089029

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: F04D29/66 ,  F02C3/04 ,  F02C6/00 ,  F04D25/06 ,  F04D27/00 ,  F02C9/16

CPC classification number: F04D29/661 ,  F02C3/04 ,  F02C6/00 ,  F02C9/16 ,  F04D25/06 ,  F04D27/004 ,  F05D2220/76

Abstract: A gas turbine engine comprises an engine core and an electric fan array. The engine core includes a compressor, a combustor, and a turbine. The compressor compresses and delivers air to the combustor. The combustor mixes fuel with the compressed air received from the compressor and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor are directed into the turbine to cause the turbine to rotate about an axis and drive the compressor. The electric fan array may include at least two non-concentric fans having parallel shafts.

公开(公告)号：US11834961B2

公开(公告)日：2023-12-05

申请号：US18162108

申请日：2023-01-31

Applicant: Rolls-Royce Corporation

Inventor： Brett Barker

IPC: F01D5/18

CPC classification number: F01D5/181 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/20

Abstract: A dual-wall airfoil configured for coolant transfer includes a spar having a pressure side wall and a suction side wall each including raised features on an outer surface thereof. An interior of the spar includes coolant cavities. An inner surface of a pressure side coversheet is in contact with the raised features on the outer surface of the pressure side wall so as to define pressure side flow pathways between the pressure side wall and the pressure side coversheet, and an inner surface of a suction side coversheet is in contact with the raised features on the outer surface of the suction side wall so as to define suction side flow pathways between the suction side wall and the suction side coversheet. The pressure side flow pathways and/or the suction side flow pathways include cooling circuit(s) configured to transfer coolant between the coolant cavities.

公开(公告)号：US11820716B2

公开(公告)日：2023-11-21

申请号：US16655565

申请日：2019-10-17

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

Inventor： Ted Freeman ,  Aaron Sippel ,  Robert Shinavski ,  Chris Barrett

IPC: C04B35/573 ,  C04B35/628 ,  C04B35/80

CPC classification number: C04B35/573 ,  C04B35/62863 ,  C04B35/62884 ,  C04B35/80 ,  C04B2235/3826 ,  C04B2235/5244 ,  C04B2235/5256 ,  C04B2235/614 ,  C04B2235/945

Abstract: A method of fabricating cooling features on a CMC component may comprise compressing a fabric preform within tooling including holes and/or recesses facing the fabric preform. During the compression, portions of the fabric preform are pushed into the holes and/or recesses. Gases are delivered through the tooling to deposit a matrix material on exposed surfaces of the fabric preform while the fabric preform is being compressed. The matrix material builds up on the portions of the fabric preform pushed into the holes and/or recesses, and a rigidized preform with surface protrusions is formed. The tooling is removed, and the rigidized preform is densified, thereby forming a CMC component including raised surface features.

公开(公告)号：US11802490B2

公开(公告)日：2023-10-31

申请号：US17412218

申请日：2021-08-25

Applicant: Rolls-Royce Corporation

Inventor： Christopher D. Hall ,  William B. Bryan ,  Daniel E. Molnar, Jr.

IPC: F01D17/16 ,  F01D7/02 ,  F01D17/06

CPC classification number: F01D17/162 ,  F01D7/02 ,  F01D17/06 ,  F05D2240/12 ,  F05D2250/90 ,  F05D2260/56

Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of outlet guide vanes including a first outlet guide vane configured to rotate to a first angle so as to redirect the fan exit air in a first direction and a second outlet guide vane configured to rotate to a second angle so as to redirect the fan exit air in a second direction. The second outlet guide vane is located at a different circumferential position than the first outlet guide vane.

公开(公告)号：US11788429B2

公开(公告)日：2023-10-17

申请号：US17412226

申请日：2021-08-25

Applicant: Rolls-Royce Corporation

Inventor： Christopher D. Hall ,  William B. Bryan ,  Daniel E. Molnar, Jr.

IPC: F01D17/16 ,  F01D17/02 ,  F01D17/06

CPC classification number: F01D17/162 ,  F01D17/02 ,  F01D17/06 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2270/102 ,  F05D2270/304

Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of vanes configured to rotate to redirect the fan exit air in a first direction, and a second plurality of vanes located downstream of the first plurality of vanes. The second plurality of vanes are configured to rotate to redirect the fan exit air flowing in the first direction in a second direction to minimize losses created by distortions in fan inlet air and created by the first vanes.

公开(公告)号：US20230321793A1

公开(公告)日：2023-10-12

申请号：US18150403

申请日：2023-01-05

Applicant: Rolls-Royce Corporation

Inventor： Quinlan Yee Shuck

IPC: B24D18/00 ,  B22F10/00 ,  B22F3/00 ,  B22F7/00 ,  B22F7/02 ,  B22F1/145 ,  B22F10/25 ,  B22F12/41 ,  B22F10/364 ,  B22F10/38

CPC classification number: B24D18/0054 ,  B22F10/00 ,  B22F3/003 ,  B22F7/008 ,  B22F7/02 ,  B22F1/145 ,  B22F10/25 ,  B22F12/41 ,  B22F10/364 ,  B22F10/38 ,  B22F2203/00 ,  B22F2303/20 ,  B22F2999/00

Abstract: A system may include a powder source; a powder delivery device; an energy delivery device; and a computing device. The computing device may be configured to: control the powder source to deliver metal powder to the powder delivery device; control the powder delivery device to deliver the metal powder to a surface of an abrasive coating; and control the energy delivery device to deliver energy to at least one of the abrasive coating or the metal powder to cause the metal powder to be joined to the abrasive coating.

公开(公告)号：US11781603B2

公开(公告)日：2023-10-10

申请号：US17930239

申请日：2022-09-07

Applicant: Rolls-Royce Corporation

Inventor： Joseph D. Black

IPC: F16D13/72 ,  F16D13/66 ,  F16D13/24

CPC classification number: F16D13/72 ,  F16D13/24 ,  F16D13/66

Abstract: In examples, a cone clutch assembly includes an inner cone member rotationally coupled to a first shaft, the inner cone member defining a first friction surface; and an outer cone member rotationally coupled to a second shaft, the outer cone member defining a second friction surface opposing the first friction surface. The inner cone member and outer cone member may be selectively engaged and disengaged from another. When the inner cone member is engaged with the outer cone member, the first friction surface of the inner cone member frictionally engages the second friction surface of the outer cone member such that rotational motion is transferred between the inner cone member and the outer cone member. The inner cone member includes at least one hole including an inlet near a front edge of the inner cone member and that extends through the inner cone member adjacent to the first friction surface.

公开(公告)号：US11746659B2

公开(公告)日：2023-09-05

申请号：US17561617

申请日：2021-12-23

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

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

IPC: F01D5/16 ,  F01D5/14

CPC classification number: F01D5/16 ,  F01D5/147 ,  F05D2260/961

Abstract: An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a shear-thickening fluid disposed in the cavity. A viscosity of the shear-thickening fluid increases in response to the airfoil experiencing an aeromechanic response or vibrations such that the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.