公开(公告)号：US20210340875A1

公开(公告)日：2021-11-04

申请号：US17376632

申请日：2021-07-15

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Sven SCHRAPE ,  Bernhard MÜCK ,  Jens NIPKAU ,  Thomas GIERSCH ,  Frank HEINICHEN ,  John DODDS

IPC: F01D5/14

Abstract: A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N≥2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.

公开(公告)号：US20210332713A1

公开(公告)日：2021-10-28

申请号：US16856752

申请日：2020-04-23

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

Inventor： Keith Sadler ,  Ted J. Freeman ,  Aaron D. Sippel ,  Alexandra Baucco

IPC: F01D11/08 ,  F01D25/24

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

公开(公告)号：US11156118B2

公开(公告)日：2021-10-26

申请号：US16934052

申请日：2020-07-21

Applicant: ROLLS-ROYCE plc

Inventor： Guy D. Snowsill ,  Robert J. Irving

IPC: F01D11/08 ,  F01D11/00 ,  F01D17/00 ,  F01D25/16 ,  F02C7/06 ,  F02C7/36

Abstract: A gas turbine is provided for an aircraft comprising an engine core and a core flow path, a fan, a front drum cavity arranged radially inward of the core flow path, and a front bearing chamber. The front drum cavity comprises a front drum inlet, for providing air to the front drum cavity from the core air flow, located downstream of a stage of the compressor, and a front drum outlet, for ejecting air from the front drum cavity to the fan air flow, located axially between the fan and the compressor. The front drum inlet is through a seal, and the front drum outlet is through a spaced gap.

公开(公告)号：US11149647B2

公开(公告)日：2021-10-19

申请号：US16679568

申请日：2019-11-11

Applicant: ROLLS-ROYCE plc

Inventor： Stephen M. Husband ,  Ahmed M Y Razak ,  Paul R. Miller

IPC: F02C7/26 ,  F02C3/06 ,  F02C9/22 ,  F04D27/00

Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: increasing an angular velocity of a low pressure compressor; determining if an exit pressure of the low pressure compressor is equal to or greater than a first threshold pressure; in response to determining that the exit pressure of the low pressure compressor is equal to or greater than the first threshold pressure, controlling rotation of the low pressure compressor using a first electrical machine and controlling rotation of a high pressure compressor using a second electrical machine, to increase angular velocity of the high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a second threshold pressure.

公开(公告)号：US11149581B2

公开(公告)日：2021-10-19

申请号：US16692617

申请日：2019-11-22

Applicant: Rolls-Royce plc ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Michael J. Whittle ,  Anthony G. Razzell ,  Stephen I. Harris

IPC: F01D21/00 ,  F02C7/00

Abstract: A component for use in a gas turbine engine includes a component body, and a damage-indicative coating. The damage-indicative coating is configured to change from an intact state in which the damage-indicative coating has a first appearance to a damaged state in which the damage-indicative coating has a second appearance.

公开(公告)号：US11149567B2

公开(公告)日：2021-10-19

申请号：US16133187

申请日：2018-09-17

Applicant: Rolls-Royce Corporation ,  Rolls-Royce plc

Inventor： Michael J. Whittle ,  Daniel Kent Vetters ,  Eric Koenig

IPC: F01D9/04 ,  F01D5/28

Abstract: An airfoil assembly includes a roller joint formed between a ceramic airfoil portion and a carrier allowing sliding (rolling) radial movement therebetween to accommodate thermal growth disparity.

公开(公告)号：US20210316418A1

公开(公告)日：2021-10-14

申请号：US17176456

申请日：2021-02-16

Applicant: Rolls-Royce plc

Inventor： Andrew J LEGGETT ,  Grant J GIBSON

IPC: B24C1/10

Abstract: An article and a method of manufacturing the article is disclosed. The method includes providing the article including a substrate and a coating at least partially disposed on the substrate. The coating includes an outer surface. The coating further includes platinum and chromium. The method further includes applying cold work to the outer surface of the coating to produce a cold-worked layer extending from the outer surface of the coating to a cold work depth. The cold-worked layer includes approximately 45% cold work. The cold work depth is between about 30 microns to about 150 microns from the outer surface of the coating.

公开(公告)号：US11146382B2

公开(公告)日：2021-10-12

申请号：US16391613

申请日：2019-04-23

Applicant: ROLLS-ROYCE plc

Inventor： Bryan L. Lapworth

IPC: G06F21/60 ,  H04L9/06 ,  G06F16/25

Abstract: Method and system for cryptographic transformation of a structured data set. The structured data set is partitioned into a first subset and a plurality of further subsets for encryption in parallel. The subsets are divided into a plurality of blocks of predetermined size. A first block for each subset is identified as well as a location of each further block in said subset relative to said first block of its subset. Cryptographic transformation of the data subsets is performed using a key according to a block chain process and an offset value for the first block of each subset from the first block of the first subset is logged. The process allows a block chain to be broken into part way in the chain. The process may allow different partitioning to be used for decryption than was used for encryption, thereby allowing parallel processing on varying numbers of computational cores.

公开(公告)号：US20210310420A1

公开(公告)日：2021-10-07

申请号：US17223200

申请日：2021-04-06

Applicant: ROLLS-ROYCE PLC

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F02C6/20 ,  F16H1/28 ,  F16H57/08 ,  F16H57/02 ,  F16C17/03

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines, including a gearbox for an aircraft gas turbine engine, the gearbox including: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

公开(公告)号：US20210310418A1

公开(公告)日：2021-10-07

申请号：US17197279

申请日：2021-03-10

Applicant: ROLLS-ROYCE PLC

Inventor： Mark SPRUCE

IPC: F02C7/36 ,  F16H57/02 ,  F16H1/28 ,  F16H57/08 ,  F02C1/00 ,  F16C17/02

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.