公开(公告)号：US20210222630A1

公开(公告)日：2021-07-22

申请号：US17061002

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE CORPORATION ,  ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

Inventor： Mark D. TAYLOR ,  Erik JANKE ,  Rory D. STIEGER ,  Daniel SWAIN

IPC: F02C7/36 ,  F02C3/10

Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator turbine is a single stage turbine having a specific work of from 200 to 350 kilojoules per kilogram, said specific work being the power output of the turbine per unit mass flow therethrough.

公开(公告)号：US20210122488A1

公开(公告)日：2021-04-29

申请号：US17061079

申请日：2020-10-01

Applicant: ROLLS-ROYCE PLC ,  ROLLS-ROYCE CORPORATION

Inventor： Daniel SWAIN ,  Rory D. STIEGER ,  Mark D. TAYLOR

IPC: B64D41/00 ,  B64D27/10 ,  F02C3/08 ,  F02C6/00 ,  H02K11/33

Abstract: An auxiliary power unit (10) for an aircraft (1) comprises a gas turbine engine comprising an engine core (12). The engine core comprises a core compressor (14) and core turbine (18) coupled by a core shaft (24). The auxiliary power unit further comprises a load spool comprising a load compressor (30), a load turbine (20) and a permanent magnet electric machine (28), each being coupled by a load shaft (26). The load shaft (26) and core shaft (24) are configured to rotate independently of one another.

公开(公告)号：US20220235698A1

公开(公告)日：2022-07-28

申请号：US17723736

申请日：2022-04-19

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE CORPORATION

Inventor： Rory D. STIEGER ,  Daniel SWAIN

IPC: F02C3/08 ,  F02C7/18

Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.

公开(公告)号：US20210123387A1

公开(公告)日：2021-04-29

申请号：US17061046

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER ,  Mark D. TAYLOR

IPC: F02C7/36 ,  F01D15/10

Abstract: A turboshaft gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The rotational speeds of the turbines are dependent upon an outlet temperature of the combustor, and a speed relationship between the turbines is defined as the ratio of rotational speeds of the turbines over a running range of non-dimensional power outputs of the gas turbine engine. A first derivative of the speed relationship is from 0.9 to 1.1

公开(公告)号：US20180079510A1

公开(公告)日：2018-03-22

申请号：US15704831

申请日：2017-09-14

Applicant: ROLLS-ROYCE plc

Inventor： Marko BACIC ,  Benjamin J. SELLERS ,  Rory D. STIEGER

IPC: B64D13/04 ,  B64D27/16 ,  F04D25/02 ,  F04D27/00 ,  F02C7/32

CPC classification number: B64D13/04 ,  B64D27/16 ,  B64D2013/0603 ,  F02C7/32 ,  F04D25/02 ,  F04D27/002 ,  F04D27/0261 ,  F05D2220/323 ,  F05D2260/40 ,  F05D2270/101 ,  F05D2270/30 ,  Y02T50/671

Abstract: A control system for use in controlling a cabin blower system. The cabin blower system includes a gas turbine engine spool, a cabin blower compressor powered by the spool and arranged in use to compress fluid used in a cabin of an aircraft, and one or more control mechanisms via which the control system controls the power extracted by the cabin blower compressor from the spool. The control system is arranged in use to control the power extracted from the spool by the cabin blower compressor in accordance with one or more primary control parameters. The control system is arranged in use to alter the spool power extracted by the cabin blower compressor by comparison with the power that would have been extracted in accordance with the primary control parameters alone, in response to modifications in a secondary control parameter indicative of the commencement or occurrence of an engine transient.

公开(公告)号：US20190214887A1

公开(公告)日：2019-07-11

申请号：US16222198

申请日：2018-12-17

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER ,  Roy S. BARTLE

IPC: H02K9/20 ,  F01D15/10 ,  H02K7/18 ,  F28D15/02

CPC classification number: H02K9/20 ,  F01D15/10 ,  F05D2220/323 ,  F28D15/02 ,  H02K3/14 ,  H02K3/24 ,  H02K7/1823 ,  H02K9/197 ,  H02K9/22

Abstract: An electrical machine has a stator carrying electrical windings which protrude at opposite ends of the stator to form respective, ring-shaped end windings. The electrical machine further has a rotor having a plurality of magnetic field-producing elements for producing a rotor magnetic field which interacts with a stator magnetic field produced by the windings. The electrical machine further has a coolant bath for holding liquid coolant. The electrical machine further has a heat sink in thermal contact with at least one of the end windings, the bath and the heat sink being configured such that the heat sink is immersed in the coolant held in the bath. The heat sink defines one or more fluid pathways configured such that vapour bubbles, formed when coolant in contact with the heat sink boils, escape by rising through the heat sink.

公开(公告)号：US20190052139A1

公开(公告)日：2019-02-14

申请号：US16035921

申请日：2018-07-16

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER

IPC: H02K1/32 ,  H02K9/20 ,  H02K7/18 ,  F01D15/10

Abstract: Electrical machine apparatus comprising: a rotor having an axis of rotation and defining a cavity therein; and a conduit positioned within the cavity of the rotor, the conduit comprising an inlet arranged to receive a fluid and an outlet arranged to exhaust the fluid, the inlet having a first radial distance from the axis of rotation and the outlet having a second radial distance from the axis of rotation, the first radial distance being greater than the second radial distance.

公开(公告)号：US20180323683A1

公开(公告)日：2018-11-08

申请号：US15966037

申请日：2018-04-30

Applicant: ROLLS-ROYCE plc ,  Rolls-Royce Marine AS

Inventor： Rory D. STIEGER ,  Astrid ROKKE

IPC: H02K9/20 ,  H02K5/20

CPC classification number: H02K9/20 ,  H02K3/22 ,  H02K3/24 ,  H02K5/20 ,  H02K9/197

Abstract: Electrical machine apparatus comprising: an elongate electrical conductor comprising a first part defining a first end and a second end, the first part defining a first conduit and a second conduit; a first coolant manifold arranged to provide coolant to the first conduit; and a second coolant manifold arranged to provide coolant to the second conduit.

公开(公告)号：US20170121031A1

公开(公告)日：2017-05-04

申请号：US15280170

申请日：2016-09-29

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER ,  Matthew MOXON ,  Mikko MATTILA

IPC: B64D33/02 ,  B64D27/14 ,  B64C21/06 ,  B64D27/02

CPC classification number: B64D33/02 ,  B64C1/0009 ,  B64C21/06 ,  B64C2230/04 ,  B64D27/02 ,  B64D27/14 ,  B64D2033/0226 ,  Y02T50/12 ,  Y02T50/166

Abstract: An aircraft (10) comprising a fuselage (12), the fuselage (10) comprising at least first and second inwardly tapering portions (20, 22) extending in a generally rearward direction from an aft end of the fuselage (12), each inwardly tapering portion (20, 22) comprising a boundary layer ingesting propulsor (36) mounted thereon.

公开(公告)号：US20170106985A1

公开(公告)日：2017-04-20

申请号：US15205648

申请日：2016-07-08

Applicant: ROLLS-ROYCE plc

Inventor： Rory D. STIEGER ,  Ivan POPOVIC

IPC: B64D13/06 ,  B64D13/02 ,  H02K7/18 ,  B64D27/16 ,  F02C9/18 ,  F02C3/13 ,  F01D15/10 ,  B64D41/00

CPC classification number: B64D13/06 ,  B64D13/02 ,  B64D27/16 ,  B64D41/00 ,  B64D2013/0603 ,  B64D2013/0611 ,  B64D2013/0618 ,  B64D2013/064 ,  B64D2013/0644 ,  B64D2013/0648 ,  F01D15/10 ,  F02C3/13 ,  F02C6/08 ,  F02C7/08 ,  F02C7/277 ,  F02C9/18 ,  F05D2220/323 ,  F05D2220/50 ,  F05D2220/76 ,  H02K7/1823 ,  Y02T50/44 ,  Y02T50/56 ,  Y02T50/671

Abstract: An aircraft pneumatic system comprises a main gas turbine engine (10) comprising a main compressor (14, 16), a recuperated auxiliary gas turbine engine (40) comprising a core compressor (42) having an inlet in fluid communication with a main compressor bleed (32) of the main gas turbine engine(10) and an environmental control system inlet in fluid communication with the main compressor bleed (32) of the main gas turbine engine (10). The environmental control system comprises a compressor (68) driveable by power provided by the auxiliary gas turbine engine (40).