公开(公告)号：US10731710B2

公开(公告)日：2020-08-04

申请号：US15450736

申请日：2017-03-06

Applicant: Rolls-Royce Corporation

Inventor： Matthew Tyler Bouton ,  Kevin Beckner ,  Andy Copeland ,  Matt Starr ,  Doug Schwerin ,  Kyle Hassler

IPC: F16D13/68 ,  F16D13/52 ,  F16D13/69 ,  F16D13/64 ,  B64D35/00 ,  B64C29/00 ,  F02C7/36 ,  B64D27/10

Abstract: A clutch for a lift fan comprising at least one output shaft lug key positioned in a keyway of at least two output clutch plates and extending axially from one to the other of the two output clutch plates. The output shaft lug key couples the rotation of the output clutch plates to the rotation an output shaft and allows axial movement of the two output clutch plates relative the output shaft lug key. The output shaft has an outer radial surface and an oppositely disposed inner radial surface, and the inner surface of the output shaft lug key extends radially to the seat of the keyway.

公开(公告)号：US10731660B2

公开(公告)日：2020-08-04

申请号：US16104671

申请日：2018-08-17

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Albert Moncada ,  David Templin

IPC: F04D29/44 ,  F01D9/04

Abstract: According to some aspects of the present disclosure, a diffuser for a centrifugal compressor is provided. The diffuser may comprise an outerband casing and an innerband casing. The outerband casing may comprise an annular flowpath boundary member that has a flowpath boundary surface. The flowpath boundary member may define a plurality of vane-receiving pockets spaced about a circumference of the member. The innerband casing may comprise an annular flowpath boundary member that has a flowpath boundary surface. The flowpath boundary member may comprise a plurality of vanes spaced about a circumference of the member. Each of said plurality of vanes may comprise a vane body that extends from the flowpath boundary surface, a platform head that has a lateral dimension normal to the length of the vane body greater than the lateral dimension of the vane body, and a fillet between the platform head and the vane body. The innerband casing may be positioned so that the platform head of each of the plurality of vanes is received in a respective vane-receiving pocket defined by the flowpath boundary member of the outerband casing. When received, the fillet of each of the plurality of vanes may be adjacent the flowpath boundary surface of the flowpath boundary member of said outerband casing. The flowpath boundary surfaces of each of said casings and said vanes define a fluid flowpath in said diffuser.

公开(公告)号：US10731481B2

公开(公告)日：2020-08-04

申请号：US15340663

申请日：2016-11-01

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

Inventor： Daniel K. Vetters ,  Ted J. Freeman ,  James Glen Schwefel ,  Phil Bastnagel

IPC: F01D5/28 ,  F01D5/30 ,  F01D5/18 ,  F01D11/00

Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.

公开(公告)号：US10717681B2

公开(公告)日：2020-07-21

申请号：US14958180

申请日：2015-12-03

Applicant: Rolls-Royce Corporation

Inventor： Sean Erin Landwehr ,  Benjamin John Bowin Lai ,  Adam Lee Chamberlain

IPC: B32B38/00 ,  C04B37/00 ,  C04B35/80 ,  B29C70/00 ,  C04B35/565

Abstract: A method of preparing a ceramic matrix composite (CMC) component that includes a protective ceramic layer comprises adhering at least one flexible ceramic tape to a ceramic fiber preform, where the at least one flexible ceramic tape comprises ceramic particles dispersed in an organic binder phase. After the adhering, the at least one flexible ceramic tape is heated to a temperature sufficient to volatilize the organic binder phase, thereby forming a porous ceramic layer on at least a portion of the ceramic fiber preform. After the heating and volatilizing, the ceramic fiber preform and the porous ceramic layer are infiltrated with a molten material, thereby forming a CMC component including, on at least a portion thereof, a protective ceramic layer.

公开(公告)号：US20200224769A1

公开(公告)日：2020-07-16

申请号：US16697398

申请日：2019-11-27

Applicant: Rolls-Royce Corporation

Inventor： Joseph Dean Black

IPC: F16J15/34

Abstract: Systems and methods are presented for sealing a higher pressure fluid cavity from a lower pressure fluid cavity in a rotating machine. The cavities are at least partially disposed between a rotatable shaft and a housing. The seal assembly comprises a runner mounting assembly, a circumferential ceramic runner, a carbon seal ring, and an annular seal member. The carbon seal ring is sealing engaged with the housing and at least a portion of the runner to thereby form a boundary between the higher pressure fluid cavity and the lower pressure fluid cavity. The annular seal member is coupled to the housing axially displaced from the seal ring in the lower pressure fluid cavity. The seal member has a curvilinear face surface that engages the runner.

公开(公告)号：US20200224705A1

公开(公告)日：2020-07-16

申请号：US16245788

申请日：2019-01-11

Applicant: Rolls-Royce Corporation

Inventor： Donald G. Chouinard

IPC: F16B35/04 ,  F16B21/20

Abstract: An engine assembly for use with a gas turbine engine includes a first component, a second component, and a retention locking plug. The first component is formed to define a passage that extends into the first component. The second component is received in the passage defined in the first component. The retention locking plug extends into the first component and the second component to couple the second component with the first component.

公开(公告)号：US20200217207A1

公开(公告)日：2020-07-09

申请号：US16241195

申请日：2019-01-07

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

Inventor： James Loebig ,  James Christopher Muskat ,  Christopher Dwayne DeBruhl

IPC: F01D5/18 ,  F01D9/06 ,  F01D25/12

Abstract: A member may have a primary major surface and a secondary major surface. The member may form an array of apertures extending from the primary major surface to the secondary major surface. The array of apertures includes at least one aperture comprising two or more conduits. The axis of each conduit intersects the axis of each other conduit in the aperture. The cross-section of at least one of the conduits perpendicular to its axis may be circular. In some embodiments, an aperture may comprise two or three conduits.

公开(公告)号：US10697320B2

公开(公告)日：2020-06-30

申请号：US15867309

申请日：2018-01-10

Applicant: Rolls-Royce Corporation

Inventor： Roy D. Fulayter ,  Michael G. Meyer

IPC: F01D25/04 ,  F02C7/045 ,  G10K11/178 ,  F01D5/22 ,  F01D25/28 ,  F02C7/24

Abstract: A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.

公开(公告)号：US10684149B2

公开(公告)日：2020-06-16

申请号：US15916755

申请日：2018-03-09

Applicant: Rolls-Royce Corporation

Inventor： Eric Koenig

IPC: G01F1/44 ,  F01D9/02 ,  F01D17/02 ,  F02C7/18 ,  F01D5/18

Abstract: Vanes for use in gas turbine engines and methods of measuring cooling air flow through vanes are disclosed herein. Each vane includes an airfoil and an end wall. The airfoil is shaped to interact with hot gasses moving along a primary gas path during operation of the gas turbine engine. The end wall is coupled to the airfoil and shaped to define a boundary of the primary gas path near a radial end of the airfoil. The end wall includes a platform that is exposed to the primary gas path and a projection that extends away from the platform and is located outside the primary gas path.

公开(公告)号：US10677195B2

公开(公告)日：2020-06-09

申请号：US15962178

申请日：2018-04-25

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

Inventor： Michael J. Armstrong ,  Igor Vaisman

IPC: F02K3/00 ,  F01K23/10 ,  F02K3/077 ,  F02C1/00 ,  F02C1/10 ,  F02C7/08 ,  F02C7/141 ,  F02C7/18 ,  F22B3/08 ,  F01K25/10 ,  F02C6/20 ,  F02C3/10 ,  F02K99/00 ,  F02C7/143 ,  F02C3/13 ,  F02C3/04

Abstract: A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.