公开(公告)号：US20180100573A1

公开(公告)日：2018-04-12

申请号：US15703535

申请日：2017-09-13

Applicant: ROLLS-ROYCE plc

Inventor： Jason J. MADGE ,  Jonathan P. BRADLEY

IPC: F16H57/023 ,  F16H1/28 ,  F16H57/08 ,  F02C7/36

CPC classification number: F16H57/023 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  F16H1/2836 ,  F16H57/0031 ,  F16H57/0479 ,  F16H57/082

Abstract: A planetary gear box assembly, comprises a sun gear and a plurality of planet gears in meshing engagement with the sun gear; the planet gears in meshing engagement with a ring gear which encircles the plurality of planet gears, each planet gear mounted for rotation in a planet carrier by means of a bearing pin wherein a bore in the planet carrier for receiving the bearing pin is parallel. The bearing pin includes a small axially tapered section adjacent one or both ends and the assembly further comprises a tapered sleeve configured to interference fit between a radially inner wall surface of the parallel bore and a radially outer surface of the or each axially tapered section.

公开(公告)号：US20180100403A1

公开(公告)日：2018-04-12

申请号：US15705804

申请日：2017-09-15

Applicant: ROLLS-ROYCE plc

Inventor： Anthony J. RAWLINSON

IPC: F01D9/04 ,  F01D5/30 ,  F01D5/08

CPC classification number: F01D9/044 ,  F01D5/081 ,  F01D5/303 ,  F01D5/3061 ,  F05D2230/237 ,  F05D2230/64 ,  F05D2240/10 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/30

Abstract: A stator assembly comprises an annular platform (1) defining a boundary of an annulus and a plurality of guide vanes (2) for arranging in a circumferential array on the annular platform (1). The platform (1) includes a circumferential array of slots each slot having, at a first end, walls converging (3) from an annulus facing side towards an opposite side of the platform and then extending parallel (4) towards a second end. One or more cooling holes (5) is arranged in a wall (3,4) of the slot. Each vane (2) includes a root portion (7) which converges in a first region (8) distal to the root end and then extends parallel towards the root end in a second region (9). The root portion (7) is configured to engage in a slot of the platform (1) with the first region (8) abutting a convergent wall portion (3) of the slot and the second region (9) spaced from a parallel wall (4) of the slot. At least one bore (11a, 12a) is provided in a parallel wall (4) of each slot and at least one bore (11b, 12b) is also provided in the second region of the root portion (7). The bores (11a, 11b; 12a, 12b) in the two components are positioned to align when a vane (2) is engaged in a slot. The aligning bores (11a, 11b; 12a, 12b) together are configured to receive a pin (13) for mechanically securing the vane in the slot. A braze joint (14) may be added between the root portion (7) and parallel slot walls 4.

公开(公告)号：US20180095134A1

公开(公告)日：2018-04-05

申请号：US15702182

申请日：2017-09-12

Applicant: ROLLS-ROYCE plc

Inventor： Sivakumar NADARAJAN ,  Amit GUPTA ,  Vaiyapuri VISWANATHAN ,  Chandana GAJANAYAKE

IPC: G01R31/34 ,  G06F17/30 ,  H02P9/10

CPC classification number: G01R31/346 ,  F02C3/04 ,  G01R31/343 ,  G06F16/285 ,  H02P9/107 ,  H02P29/0243 ,  H02P2101/25 ,  H02P2103/20

Abstract: A method of classifying a stator winding fault in a brushless synchronous generator includes measuring an electrical parameter of the stator winding and classifying the fault by calculating positive or negative sequence harmonics of the parameter and comparing one or more harmonic component to a threshold.

公开(公告)号：US20180087395A1

公开(公告)日：2018-03-29

申请号：US15714082

申请日：2017-09-25

Applicant: ROLLS-ROYCE plc

Inventor： Adrian L. HARDING

IPC: F01D11/22 ,  F01D9/04 ,  F01D17/16 ,  F01D25/24

CPC classification number: F01D11/22 ,  F01D9/041 ,  F01D9/042 ,  F01D11/16 ,  F01D17/16 ,  F01D25/24 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/50

Abstract: A gas turbine engine comprising a rotor blade, an inner casing and an outer casing, a guide vane, located upstream of the rotor blade and between the inner and outer casing, the guide vane comprising a vane contact member, wherein the guide vane is configured to pivot upon axial displacement of the inner casing relative to either or both of the outer casing and the rotor blade; and, a seal segment located radially outwardly of the rotor blade and mounted for radial displacement relative to the rotor blade; wherein at least a portion of the seal segment axially overlaps, and slidably engages a downstream end of the guide vane so that a pivoting of the guide vane causes the vane contact member to undergo a radially outward displacement which causes a radially outward displacement of at least a portion of the seal segment.

公开(公告)号：US20180079515A1

公开(公告)日：2018-03-22

申请号：US15684265

申请日：2017-08-23

Applicant: ROLLS-ROYCE PLC

Inventor： Richard HARWOOD ,  Kalyani G. MENON ,  Joseph PALMER ,  Ivan POPOVIC

IPC: B64D27/24

CPC classification number: B64D27/24 ,  B61C5/00 ,  B63H21/17 ,  B63H21/20 ,  B64D27/02 ,  B64D27/10 ,  B64D2027/026 ,  H02J3/005 ,  H02J3/02 ,  H02J3/46 ,  H02J7/34 ,  H02P5/74 ,  Y02T30/10 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T70/5209 ,  Y02T70/5236 ,  Y02T90/46

Abstract: An aircraft propulsion system (10) comprises at least first and second electrical generators (15a, 15b), each being configured to provide electrical power to a respective first and second AC electrical network (16a, 16b). The system (10) further comprises at least first and second AC electrical motors (19a, 19b) directly electrically coupled to a respective AC network (16a, 16b) and coupled to a respective propulsor (4), and a DC electrical network electrically coupled to the first and second AC networks (16a, 16b) via respective first and second AC to DC converters (17a, 17b), and to a further electrical motor 19c), the further electrical motor (19c) being coupled to a propulsor (4).

公开(公告)号：US09923551B2

公开(公告)日：2018-03-20

申请号：US15292323

申请日：2016-10-13

Applicant: ROLLS-ROYCE plc

Inventor： Lily Rachmawati ,  Eng Yeow Cheu ,  Anna Swider ,  Martijn De Jongh ,  Eivind Vinje

IPC: H03H21/00 ,  B63J99/00

CPC classification number: H03H21/0027 ,  B63J2099/006 ,  G06F17/10 ,  H03H21/002

Abstract: The invention is a method that combines the following components: a high pass filter designed to have sufficiently small phase delay and roll-off value in transition band as well as sufficiently good attenuation; a distortion detection and reconstruction introduced by the application of the high pass filter by extraction the significant frequency components in relevant frequency band; a signal compensation that reshapes the output of the high pass filter by matching the filter's phase delay and attenuation characteristics so as to approximate low frequency component extraction that would be produced by an ideal filter (very sharp frequency transition and no delay); a time-domain detection and correction method that addresses special circumstances under which the compensation would be inaccurate to achieve real-time estimate in normal circumstances, and a time-domain correction method during and immediately after sudden changes in composite signal (spike) is detected.

公开(公告)号：US20180073382A1

公开(公告)日：2018-03-15

申请号：US15692619

申请日：2017-08-31

Applicant: ROLLS-ROYCE PLC

Inventor： Matthew MOXON

IPC: F01D11/24 ,  F04D27/00

CPC classification number: F01D11/24 ,  F01D17/145 ,  F04D27/001 ,  F04D27/002 ,  F04D27/0246 ,  F05D2220/323 ,  F05D2240/307 ,  F05D2260/82 ,  F05D2270/11 ,  F05D2270/30

Abstract: A method of controlling a rotor tip clearance in a gas turbine engine (10). The method comprises determining an engine or component remaining useful life Tr, and controlling a tip clearance control arrangement (38) to maintain a rotor tip clearance (36) at a target tip clearance Dtarget. The target tip clearance Dtarget is determined in accordance with a function of remaining engine life Tr.

公开(公告)号：US20180073370A1

公开(公告)日：2018-03-15

申请号：US15683339

申请日：2017-08-22

Applicant: ROLLS-ROYCE plc

Inventor： Martin MOTTRAM ,  David J. HUNT ,  Haidong LI ,  Shahrokh SHAHPAR ,  Stefano CALONI

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/141 ,  F01D5/20 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/314 ,  F05D2250/52 ,  F05D2260/202

Abstract: A blade includes a root and an elongate portion extending to a tip, the elongate portion having an aerofoil-shaped cross-section. The aerofoil has leading and trailing edges, and suction and pressure sides. The tip includes a squealer defining a gutter at the tip, the squealer extending from the trailing edge along the entirety of a first of the suction and pressure sides, around the leading edge and partly along a second of the suction and pressure sides leaving a gap between the trailing edge and an end of the wall. A main trailing edge cooling channel extends within the elongate portion in a direction from root to tip adjacent the trailing edge and exits into the gutter. The main trailing edge cooling channel includes a bend just downstream of the exit, the exit displaced from a camber line of the blade elongated portion towards the second side.

公开(公告)号：US20180073106A1

公开(公告)日：2018-03-15

申请号：US15696516

申请日：2017-09-06

Applicant: ROLLS-ROYCE plc

Inventor： Mark C. HARDY ,  Grant J. GIBSON ,  Gavin J. BAXTER ,  Yogiraj PARDHI

IPC: C22C19/05 ,  C22C1/02 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00 ,  B23K15/00 ,  B23K26/342

Abstract: The novel nickel-base superalloy useful in an additive manufacturing process or a powder-based manufacturing process includes the following composition in wt %: Cr 8.0-8.5; Co 9.0-9.5; Mo 0.4-0.6; W 9.3-9.7; Ta 2.9-3.6; Al 4.9-5.6; Ti 0.2-1.0; Hf 0-0.05; C 0.005-0.03; B 0.005-0.02; Zr 0.005-0.1; Nb 0.2-1; Mn 0-0.6; and S 0-0.002 (≦20 ppm); the balance nickel and incidental elements and unavoidable impurities.

公开(公告)号：US09915169B2

公开(公告)日：2018-03-13

申请号：US14810551

申请日：2015-07-28

Applicant: ROLLS-ROYCE PLC

Inventor： Ian Tibbott ,  Dougal Richard Jackson

IPC: F01D25/12 ,  F01D9/04 ,  F01D5/18 ,  F01D9/02

CPC classification number: F01D25/12 ,  F01D5/186 ,  F01D5/187 ,  F01D9/023 ,  F01D9/041 ,  F01D9/047 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/81 ,  F05D2250/14 ,  F05D2250/18 ,  F05D2250/184 ,  F05D2260/202

Abstract: An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas upstream of the vanes to reduce the mainstream gas temperature adjacent the end-wall, wherein the cooling holes are arranged in one or more circumferentially extending rows and wherein the axial position of the cooling holes in the or each row varies.