公开(公告)号：US12017790B2

公开(公告)日：2024-06-25

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

CPC classification number: B64D41/00 ,  B64D27/10 ,  F02C3/08 ,  F02C6/00 ,  H02K11/33 ,  F05D2220/32 ,  F05D2220/50

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：US11566562B2

公开(公告)日：2023-01-31

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：US12172757B2

公开(公告)日：2024-12-24

申请号：US18155351

申请日：2023-01-17

Applicant: ROLLS-ROYCE plc ,  Rolls-Royce Corporation

Inventor： Christopher A. Murray ,  Nicholas Howarth ,  Daniel Swain ,  Ian J. Bousfield

IPC: B64D13/06 ,  F02C7/32 ,  F04D25/04 ,  F04D29/68

Abstract: There is provided a blower system for providing air to an airframe system, comprising a rotor configured to be mechanically coupled to a spool 440 of a gas turbine engine, wherein the rotor is configured to: in a blower mode, be driven to rotate by the spool to discharge air to an airframe discharge port for supply to an airframe system; and, in an engine drive mode, receive air from an external air source via an impingement port that is configured to direct the received air onto the rotor and thereby drive the rotor to rotate to drive the spool to.

公开(公告)号：US11339714B2

公开(公告)日：2022-05-24

申请号：US17061057

申请日：2020-10-01

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.