公开(公告)号：US20210301760A1

公开(公告)日：2021-09-30

申请号：US16836080

申请日：2020-03-31

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

Inventor： David L. Sutterfield ,  Todd S. Taylor ,  Jack D. Petty ,  Andrew Sanderson ,  Bryan H. Lerg

IPC: F02K1/34 ,  F02K1/70

Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

公开(公告)号：US20210293174A1

公开(公告)日：2021-09-23

申请号：US16822860

申请日：2020-03-18

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Kerry J. Lighty ,  Paul O'Meallie ,  Sean Morgan ,  Alan W. Smith

IPC: F01P3/22 ,  F01P11/02

Abstract: A cooling system includes a first cooling loop, a second cooling loop and a heat exchanger configured to transfer heat from the first cooling loop to the second cooling loop. The first cooling loop includes a flow restrictor, an inertial separator, and a pressure relief valve cooperating to effect diversion of vapor present in the first cooling loop due to a leak between the first cooling loop and the second cooling loop.

公开(公告)号：US11092027B2

公开(公告)日：2021-08-17

申请号：US16688562

申请日：2019-11-19

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

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

IPC: F01D11/08 ,  F01D25/24

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.

公开(公告)号：US11073083B2

公开(公告)日：2021-07-27

申请号：US16269267

申请日：2019-02-06

Applicant: Rolls-Royce North American Technologies, Inc. ,  University of Virginia Patent Foundation

Inventor： Philip H. Snyder ,  Eric Loth ,  Dominic L. Barone

IPC: F02C7/05 ,  B64D33/02 ,  F02C7/052 ,  B01D45/06 ,  B01D45/16

Abstract: An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.

公开(公告)号：US11053806B2

公开(公告)日：2021-07-06

申请号：US16661572

申请日：2019-10-23

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

Inventor： Aaron D. Sippel ,  Daniel K. Vetters ,  Jun Shi ,  David J. Thomas ,  Andrew J. Eifert ,  Peter Broadhead

IPC: F01D9/04 ,  F01D9/02 ,  F01D25/24

Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.

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：US11014686B2

公开(公告)日：2021-05-25

申请号：US16167917

申请日：2018-10-23

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： David R. Trawick ,  David Loder

IPC: B64D41/00 ,  H03K17/16 ,  H02J3/00 ,  H02J1/14 ,  H02J3/38 ,  H02J1/08

Abstract: A redundant, load-sharing system and method for distributing electrical power to components in a vehicle. The system including a source of power, multiple power distribution buses, a plurality of switching devices and at least two channel controllers. The system being configured to isolate the components and power sources that are determined to be electrically noisy from the components and the power sources that are sensitive to electric noise. Each of the components may be assigned a priority based on the criticality of the component to the operation of the vehicle. In the event of at least a partial loss of power in one or more of the power distribution buses, the switching devices disconnect the components from the effected power distribution buses in reverse order of the assigned priority.

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.