公开(公告)号：US20210276692A1

公开(公告)日：2021-09-09

申请号：US17188456

申请日：2021-03-01

Applicant: Rolls-Royce plc

Inventor： Samuel O. HUTCHINSON ,  Andrew SMYTH

IPC: B64C11/30 ,  B64C11/06 ,  B64D27/02

Abstract: A noise mitigation system for an aircraft comprises a cyclic pitch mechanism arranged to apply a cyclic pitch schedule to rotor blades of an unducted propulsive rotor (UPR) under control of a processor. The processor receives input data corresponding to the position and attitude of the UPR, the position of one or more ground points stored in a memory and the velocity of the aircraft. If the processor determines that a ground point will enter the plane of the UPR, a control signal is output to the cyclic pitch mechanism as necessary to adjust the phase of the cyclic pitch schedule such that the azimuthal position of the ground point on entry to the plane of the UPR lies within an azimuthal interval over which the blade pitch of the cyclic pitch schedule is below its average value, thus reducing noise in the direction of the ground point.

公开(公告)号：US11105207B2

公开(公告)日：2021-08-31

申请号：US16539688

申请日：2019-08-13

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：US11098656B2

公开(公告)日：2021-08-24

申请号：US17062272

申请日：2020-10-02

Applicant: ROLLS-ROYCE PLC

Inventor： Mark Spruce

IPC: F02C7/36 ,  F16H1/28 ,  F16H57/02

Abstract: A gas turbine engine for an aircraft has an engine core having a turbine, compressor, and core shaft connecting the turbine and compressor; a fan upstream the engine core, the fan having fan blades; and a gearbox. The gearbox receives an input from a core shaft and outputs drive to a fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and has a sun gear, planet gears, ring gear, and planet carrier on which the planet gears are mounted. The gearbox has a gear mesh stiffness between the planet gears and the ring gear and a gear mesh stiffness between the planet gears and the sun gear. The gear mesh stiffness between the planet gears and the ring gear divided by that between the planet gears and the sun gear is in the range from 0.90 to 1.28.

公开(公告)号：US20210254501A1

公开(公告)日：2021-08-19

申请号：US17235234

申请日：2021-04-20

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J BOUSFIELD ,  Duncan A MACDOUGALL

IPC: F01D25/02 ,  F01D5/14 ,  F04D29/32

Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.

公开(公告)号：US20210254489A1

公开(公告)日：2021-08-19

申请号：US17100388

申请日：2020-11-20

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE Corporation

Inventor： Simon J. Donovan ,  Peter E. Daum ,  Christopher P. Heason

IPC: F01D11/12 ,  B23K26/00 ,  B23K26/08 ,  B23K26/144 ,  B23K26/342 ,  B33Y10/00 ,  B33Y50/02 ,  C22C19/05 ,  B33Y80/00

Abstract: A method of forming a wall structure on a substrate comprises depositing, by additive-layer, powder-fed, laser-weld deposition apparatus, a plurality of material layers overlying one another on the substrate to form the wall structure. Each material layer of the plurality of material layers has (a) a layer thickness, measured in a direction locally perpendicular to a profile of the substrate, of no greater than about 350 μm and (b) a layer width, measured in a direction locally parallel to the profile of the substrate, of no greater than about 1200 μm.

公开(公告)号：US20210246811A1

公开(公告)日：2021-08-12

申请号：US17169624

申请日：2021-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Alan R. MAGUIRE ,  Richard SHARPE ,  Neil J. DAVIES

IPC: F01D25/20 ,  F01M1/02

Abstract: A system for supplying lubricant to a component of a gas turbine engine having a fan shaft is provided. The system includes a pump drivably couplable to the fan shaft for pumping lubricant to the component. The pump includes an inlet for receiving lubricant from a lubricant source, an outlet for outputting lubricant to the component and a swashplate movable between at least a first position and a second position. The system also includes a swashplate actuator for actuating the swashplate between the first position and the second position according to whether the fan shaft is rotating in a forward direction or a reverse direction opposite to the forward direction.

公开(公告)号：US11085643B2

公开(公告)日：2021-08-10

申请号：US16254705

申请日：2019-01-23

Applicant: ROLLS-ROYCE plc

Inventor： Richard Freeman ,  Christopher Rafferty ,  Thomas Jones ,  Matthew Murphy ,  Nicholas M. Brown

IPC: F23R3/14 ,  F23R3/28 ,  F23D14/00 ,  F23R3/10 ,  F23D11/00 ,  F23D11/38 ,  F23C7/00 ,  F23M5/08 ,  B33Y10/00 ,  B33Y80/00 ,  B29C64/153 ,  B01F5/00 ,  B01F15/00 ,  F23R3/46

Abstract: An air swirler arrangement comprises a coaxial arrangement of an inner and an outer air swirler passage. Each air swirler passage comprises a radial flow swirler. Air swirler arrangement comprises a coaxial arrangement of first, second and third members. Second member has radially extending upstream portion spaced axially from first member and a convergent portion. Third member has a radially extending upstream portion spaced axially from the upstream portion of second member and a radially inner surface having convergent and divergent downstream portions and a radially outer surface having a divergent downstream portion. First, second and third members the vanes of the radial flow swirlers is a monolithic structure. Plurality of circumferentially spaced passages are provided within the third member and each passage has an inlet in the surface and an outlet arranged to direct fluid onto the divergent portion of the surface or the surface of the third member.

公开(公告)号：US20210222880A1

公开(公告)日：2021-07-22

申请号：US17149266

申请日：2021-01-14

Applicant: Rolls-Royce plc

Inventor： Stephen C. Harding ,  Frederic Witham

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/052 ,  F02C7/18

Abstract: A combustion chamber (15) comprising a wall at least partially defining a combustion zone and having a first surface (41) facing away from the combustion zone and a second surface (43) facing the combustion zone, the wall having at least one effusion cooling aperture (69, 73) extending there-through from the first surface to the second surface, the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface, the first surface having a particle separator (84) at least partially located upstream of the inlet of the effusion cooling aperture, the particle separator projecting away from the first surface and away from the combustion zone.

公开(公告)号：US20210222632A1

公开(公告)日：2021-07-22

申请号：US17143629

申请日：2021-01-07

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W. BEMMENT ,  Pascal DUNNING

IPC: F02C9/00 ,  F02C3/04 ,  F02C7/36 ,  B64D27/10 ,  B64D31/00

Abstract: A gas turbine engine comprises a fan, a compressor, a low pressure turbine and a high pressure turbine. The fan diameter is greater than 250 cm and less than 381 cm; and the gas turbine engine has a first thrust at sea level static conditions and a second thrust at end of runway conditions; and a thrust take-off ratio greater than 1.32; wherein the thrust take-off ratio is the ratio of the first thrust to the second thrust.

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.