公开(公告)号：US20210148239A1

公开(公告)日：2021-05-20

申请号：US17096227

申请日：2020-11-12

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

Inventor： Quinlan Yee Shuck ,  Scott Nelson ,  Raymond Ruiwen Xu ,  Brandon David Ribic ,  Matthew R. Gold

IPC: F01D5/28 ,  B29C64/165 ,  B29C64/245 ,  B33Y80/00

Abstract: In general, techniques are described for fused filament fabrication of abradable coatings. An additive manufacturing system comprising a substrate defining a major surface, a filament delivery device, and a computing device may be configured to perform various aspects of the techniques. The computing device may be configured to control the filament delivery device to deposit a filament on the substrate, the filament including a powder and a binder, wherein the binder is configured to be substantially removed from the filament and the powder includes a metal or alloy configured to be sintered to form an abradable layer.

公开(公告)号：US11008882B2

公开(公告)日：2021-05-18

申请号：US16388129

申请日：2019-04-18

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Douglas David Dierksmeier

IPC: F01D11/22 ,  F01D9/04 ,  F01D25/24 ,  F01D11/14

Abstract: An assembly is disclosed for adjusting the radial position of one or more blade tracks radially encasing the blades of a turbine stage in a gas turbine engine. The assembly comprises a static turbine casing, a plurality of blade track carriers, an annular control ring, an actuator, and a plurality of blade tracks. The blade tracks have a radially inner surface that defines a flowpath boundary of the turbine stage. The blade tracks are carried by the blade track carriers, which are engaged with the annular control ring. Actuation of the actuator moves the control ring in an axial dimension and this movement is translated into an adjustment of the radial position of the blade track.

公开(公告)号：US10988035B2

公开(公告)日：2021-04-27

申请号：US16600196

申请日：2019-10-11

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

Inventor： Michael James Armstrong ,  Mark Jon Blackwelder ,  David John Howard Eames ,  Ellis Fui Hen Chong

IPC: B60L50/10 ,  B64D31/06 ,  H02P5/74

Abstract: An alternating current type electric propulsion system is described that includes an AC generator and a plurality of propulsors electrically coupled to the AC generator. A first propulsor from the plurality of propulsors includes a first motor that drives a first fan of the first propulsor at a first speed. A second propulsor from the plurality of propulsors comprises a second motor that drives a second fan of the second propulsor at a second speed that is different than the first speed.

公开(公告)号：US10974840B2

公开(公告)日：2021-04-13

申请号：US16668345

申请日：2019-10-30

Applicant: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.

Inventor： Jack D. Petty, Sr. ,  Colin Faucett ,  Kenneth M Pesyna ,  James C. Loebig

IPC: B64D33/04 ,  F02K1/82 ,  F02C3/04 ,  F02C7/24 ,  B64D27/12 ,  F01D25/30 ,  F01D9/02

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

公开(公告)号：US10969216B2

公开(公告)日：2021-04-06

申请号：US16054705

申请日：2018-08-03

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Keith Bourne ,  Matthew R. Gold ,  Benjamin Zimmerman

IPC: G01B11/06 ,  G01B21/08 ,  B05B13/04 ,  B05B12/04 ,  B05B7/22 ,  G01B11/24 ,  B05B16/00 ,  C23C4/12 ,  C23C24/04 ,  B05B12/00 ,  B05B12/12 ,  F01D5/28 ,  B05B12/08 ,  C23C4/00 ,  B05B1/30 ,  G06F17/17 ,  C23C4/134 ,  C23C4/04 ,  C23C4/131 ,  B05B7/00 ,  B05B7/20 ,  G01B21/20

Abstract: An example method that includes receiving a geometry of a component that includes a plurality of locations on a surface of the component; determining a first target trajectory including a first plurality of target trajectory points and a second target trajectory including a second plurality of target trajectory points, the first and second trajectories offset in a first direction, and the first and second plurality of trajectory points offset in a second direction; determining a respective target coating thickness of the coating based on a target coated component geometry and the geometry; and determining a respective motion vector of a coating device based on the first and second target trajectories to deposit the respective target coating thickness.

公开(公告)号：US10934879B2

公开(公告)日：2021-03-02

申请号：US16227986

申请日：2018-12-20

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

Inventor： Mark O'Leary ,  Daniel K. Vetters ,  Matthew R. Brandt ,  Ted J. Freeman

IPC: F01D11/12 ,  F01D11/00 ,  F01D25/00 ,  F01D25/12 ,  F01D25/24 ,  F01D9/04

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

公开(公告)号：US10934868B2

公开(公告)日：2021-03-02

申请号：US16128753

申请日：2018-09-12

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

Inventor： David J. Thomas ,  Ted J. Freeman ,  Aaron D. Sippel

IPC: F01D9/04 ,  F01D5/18

Abstract: A vane assembly for use in a gas turbine engine includes an airfoil, a strut, and a support member. The airfoil is configured to interact with gases flowing through a primary gas path of the engine. The strut is located in an interior region of the airfoil and configured to carry loads that act on the airfoil by the gases. The support member is configured to compensate for relative thermal expansion between the components of the vane assembly caused by heat generated during use of the engine to locate the airfoil radially in the primary gas path.

公开(公告)号：US10934866B2

公开(公告)日：2021-03-02

申请号：US15962550

申请日：2018-04-25

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Patrick Bailey

IPC: F01D7/00 ,  F04D29/36 ,  F02K3/06 ,  F04D29/32 ,  B64C11/32

Abstract: A gas turbine engine includes a fan having a plurality of fan blades configured to rotate about a central axis of the gas turbine engine. Each fan blade is configured to pivot about a pivot axis that extends radially away from the central axis to vary a pitch of the fan blade. The fan further includes a counterforce system configured to resist forces that urge the fan blades away from their pitch positions during operation of the gas turbine engine.

公开(公告)号：US10934859B2

公开(公告)日：2021-03-02

申请号：US16111749

申请日：2018-08-24

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

Inventor： Ted J. Freeman ,  Anthony Razzell ,  Michael J. Whittle

IPC: F01D5/28 ,  F01D5/30

Abstract: The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disk.

公开(公告)号：US10927957B2

公开(公告)日：2021-02-23

申请号：US16109251

申请日：2018-08-22

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Michel S. Smallwood ,  Mark A. Herbertz ,  Kenneth W. Froemming ,  Jack D. Petty

IPC: F16J15/3256 ,  F02C7/28 ,  F16J3/04 ,  F16J15/3284 ,  F16L27/111

Abstract: A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.