公开(公告)号：US20210156280A1

公开(公告)日：2021-05-27

申请号：US16694193

申请日：2019-11-25

Applicant: Rolls-Royce Corporation

Inventor： John Gebhard ,  Adam Kempers ,  Jeremy Gallagher

IPC: F01D25/20 ,  F02C7/06

Abstract: A gas turbine engine for an aircraft may include a shaft fixed to a compressor of the gas turbine engine, at least one of a turboprop and a turbofan, a power gearbox having a power output shaft fixed to the at least one of the turboprop and the turbofan, wherein the power gearbox receives an input rotation from the shaft, an auxiliary gearbox having an auxiliary output shaft powering at least one auxiliary component of the gas turbine engine, a first lubrication system, and a second lubrication system that is separated from the first lubrication system. The first lubrication systems may circulates a first lubricant through the power gearbox, and the second lubrication system may circulate a second lubricant through the auxiliary gearbox.

公开(公告)号：US11015812B2

公开(公告)日：2021-05-25

申请号：US15972309

申请日：2018-05-07

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

Inventor： Jack D. Petty, Sr. ,  John D. Holdcraft ,  Kevin M. Sauer ,  Duane A. Smith

IPC: F23R3/60 ,  F23R3/50 ,  F23R3/00 ,  F23R3/06 ,  F23M5/04

Abstract: A combustor liner assembly is provided including an inlet wall, an inner wall, an outer wall, and a plurality of fasteners. The inlet wall has an opening into a combustion chamber. The inner wall is coupled to the inlet wall at a first end of the combustor liner. The inner wall defines a radially inner end of the combustion chamber. The outer wall includes a plurality of segments. The plurality of segments define a radially outer end of the combustion chamber. A first portion of the plurality of fasteners couples each of the plurality of segments to another of the plurality of segments. A second portion of the plurality of fasteners couples at least one of the plurality of segments to the inlet wall at the first end of the combustor liner.

公开(公告)号：US20210148645A1

公开(公告)日：2021-05-20

申请号：US17097843

申请日：2020-11-13

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: F28D15/04 ,  B29C64/118 ,  B22F3/00 ,  B22F3/10 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y80/00 ,  B33Y70/10 ,  F28D15/02

Abstract: In some examples, a method for additively manufacturing a heat pipe, the method including depositing, via a filament delivery device, a filament to form a heat pipe preform, wherein the filament includes a binder and a metal or alloy powder; and sintering the heat pipe preform to form the heat pipe, the heat pipe including an outer shell, a wicking region, and a vapor transport region defined by the metal or alloy.

公开(公告)号：US20210148398A1

公开(公告)日：2021-05-20

申请号：US16684931

申请日：2019-11-15

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

Inventor： Brett Hartnagel ,  Ryan C. Humes ,  David C. Farnum

IPC: F16B39/28

Abstract: An anti-rotation device for a pair of threaded components includes a pair of ratchet interfaces and a spring element. A first ratchet interface and the spring element are movably disposed within a first threaded component, and a second ratchet interface is disposed at a mating end of a second threaded component. During relative rotation of the pair of threaded components, the ratchet interfaces engage, providing a resistance to the threaded components loosening that is greater than a resistance that the ratchet interfaces provide to the threaded components tightening. The anti-rotation device engages automatically upon relative rotation of the threaded components, and not as a separate step occurring after rotation. Additionally, the anti-rotation device may be especially useful in systems where various types of movement can cause the threaded components to loosen, and where visual access to the anti-rotation device is impeded.

公开(公告)号：US20210148250A1

公开(公告)日：2021-05-20

申请号：US16685242

申请日：2019-11-15

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

Inventor： Aaron D. Sippel ,  Ted J. Freeman

IPC: F01D25/24 ,  F01D11/08

Abstract: A turbine module includes a turbine rotor assembly, a turbine case, and a turbine shroud assembly. The turbine rotor assembly is mounted to rotate about a central reference axis. The turbine case is spaced radially outward from the turbine rotor assembly circumferentially around the central reference axis. The turbine shroud assembly includes a plurality of turbine shroud segments mounted to the turbine case. Each turbine shroud segment includes a blade track segment that faces the turbine rotor assembly and a carrier mounted to the turbine case.

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：US11009085B2

公开(公告)日：2021-05-18

申请号：US16415580

申请日：2019-05-17

Applicant: Rolls-Royce Corporation

Inventor： Donald Klemen ,  Brian S. Maners ,  Erik A. Munevar

IPC: F16D27/06 ,  F16D27/14 ,  F02C7/32

Abstract: A gearbox rigidly coupled to a static structure; a driven component rigidly coupled to another static structure; a clutch assembly floating between and coupled to the gearbox and driven component. The clutch may have aligned output and input shafts, defining an engagement surface, a bearing, and a magnetic friction plate coupled and rotating with the input shaft. The plate may have a friction-engagement face, and a magnetic flux generator. The magnetic flux generator may be rigidly coupled to a static housing and partially surrounded in the radial direction by a structure configured to reduce leakage of a magnetic flux, by defining a plurality of voids, which direct multiple passes of the magnetic flux through the engagement surface of the output shaft. The magnetic flux generator may create the magnetic flux that creates a magnetic force between the engagement face and the magnetic friction plate that causes them to engage.

公开(公告)号：US11008887B2

公开(公告)日：2021-05-18

申请号：US16229615

申请日：2018-12-21

Applicant: Rolls-Royce Corporation

Inventor： Christopher Hall ,  Matthew Kappes ,  Glenn Patterson ,  Robert Heeter

IPC: F01D21/04 ,  F01D25/24 ,  F01D25/26

Abstract: A containment assembly is disclosed for a turbofan engine. The containment assembly comprises a forward fence, an aft fence, a fan track liner, an intermediate casing member, an outer casing member, and an annular nesting cavity. The fan track liner is disposed axially between the forward and aft fences. The intermediate casing member is disposed radially outward of at least a portion of the fan track liner. The outer casing member is disposed radially outward of at least a portion of the intermediate member. The annular nesting cavity is bounded at least in part by the intermediate casing member and the outer casing member.

公开(公告)号：US11002284B2

公开(公告)日：2021-05-11

申请号：US16433089

申请日：2019-06-06

Applicant: Rolls-Royce Corporation

Inventor： Michael Nesteroff ,  Jonathan Acker ,  Nate Cooper ,  Nathan Ottow

IPC: F04D29/16 ,  F01D11/24 ,  F04D27/02 ,  F04D29/62 ,  F01D11/18 ,  F01D11/08 ,  F04D29/42 ,  F01D11/22

Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.

公开(公告)号：US11001903B2

公开(公告)日：2021-05-11

申请号：US15806957

申请日：2017-11-08

Applicant: Rolls-Royce Corporation

Inventor： Gangshu Shen ,  Nathan J. Cooper ,  Nathan Wesley Ottow ,  Robert Louis Goetz ,  John F. Matlik

IPC: C21D1/18 ,  C21D1/62 ,  C21D1/63 ,  B29C71/02 ,  C21D11/00 ,  C21D1/64

Abstract: In some examples, an apparatus includes a pallet supporting a plurality of workpieces, the pallet including through-holes structured to pass a quenching fluid. In some examples, the apparatus further includes a reservoir of quenching fluid configured to provide the quenching fluid, and a plurality of upturned wall portions extending from the pallet and substantially surrounding the exteriors of the plurality of workpieces. The plurality of upturned wall portions may be located in relative orientation to the plurality of workpieces to regulate heat transfer coefficients of the plurality of workpieces during a quenching operation.