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公开(公告)号：US20190249869A1
公开(公告)日：2019-08-15
申请号：US16248002
申请日：2019-01-15
Applicant: ROLLS-ROYCE plc
Inventor： Mark GLOVER
CPC classification number: F23D11/383 , F23R3/283 , F23R2900/00012
Abstract: A nozzle for a fuel injector of a gas turbine engine, the nozzle having an insulating air gap adjacent a conduit for carrying fuel, the air gap formed between a pair of concentrically arranged annular walls, wherein the pair of annular walls are arranged to move independently to accommodate differential thermal expansion, the nozzle further including: a channel extending circumferentially around a surface a first of the pair of annular walls, facing a second of the pair of annular walls; and a sealing member received in the channel, to close the insulating gap.
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公开(公告)号：US20190249720A1
公开(公告)日：2019-08-15
申请号：US16249187
申请日：2019-01-16
Applicant: ROLLS-ROYCE plc
Inventor： Alan R. MAGUIRE
CPC classification number: F16D3/50 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2240/61 , F05D2240/62 , F16C3/02 , F16D3/06
Abstract: A turbofan engine driveshaft comprises, in axial sequence along an axial centreline, a driving portion, and a driven portion. The driving portion has a first end and a second end. The second end of driving portion is connected to the driven portion. The driven portion comprises an annular drum having a radially inwardly facing surface, with the annular drum having a stiffener attached to the radially inwardly facing surface.The driveshaft is supported radially by a bearing assembly at the connection between the driving portion and the driven portion. The driving portion is configured to accommodate a predetermined range of movement of the outer end relative to the inner end.
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公开(公告)号：US20190249600A1
公开(公告)日：2019-08-15
申请号：US16247847
申请日：2019-01-15
Applicant: ROLLS-ROYCE PLC
Inventor： Stephen J SALT , Paul BROUGHTON , Jack CULLINAN , Christopher L GREEN
IPC: F02C7/00 , H01B13/012 , B29C59/04
CPC classification number: F02C7/00 , B29C59/04 , B29L2031/707 , F05D2230/50 , F05D2270/80 , H01B13/0023 , H01B13/012 , H01B13/01209 , H01B13/01245
Abstract: A method of manufacturing a cable harness may comprise the steps of providing a plurality of cables, wherein each cable comprises a cable inner and a coating, wherein each cable inner comprises at least one conductor, locating at least a portion of each of the plurality of cables within a mould tool, heating the portions of each of the plurality of cables such that the coating of each cable consolidates to form a common harness with a solid cross section, wherein the cable inners are arranged within the common harness.
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公开(公告)号：US10378625B2
公开(公告)日：2019-08-13
申请号：US15645512
申请日：2017-07-10
Applicant: ROLLS-ROYCE plc
Inventor： Christopher J Durling
Abstract: A ring gear arrangement, including: a ring gear mount including: a ring gear having at least one internal gear for interaction with one or more gear wheels; a ring gear stator; and, a plurality of couplings which locate the ring gear within the gear stator, each coupling having a drive arm connected to the ring gear and a resiliently deformable connection, wherein the drive arm is movable between a first position in which the ring gear is in a rest position and a second position in which the ring gear has undergone some radial or rotational movement relative to the ring gear stator, wherein movement of the drive arm from a the first position to the second position loads the resiliently deformable connection against the ring gear, wherein the resiliently deformable connection biases the drive arm to return to the first position when in the second position.
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公开(公告)号：US20190240783A1
公开(公告)日：2019-08-08
申请号：US16248909
申请日：2019-01-16
Applicant: ROLLS-ROYCE plc
Inventor： Yogiraj PARDHI
IPC: B23K26/342 , B33Y10/00 , B33Y40/00 , B33Y80/00 , B23K26/00 , B23K26/0622 , B23K26/06 , B23K26/073 , B23K26/14
CPC classification number: B23K26/342 , B22F2003/247 , B23K26/0093 , B23K26/0622 , B23K26/0626 , B23K26/073 , B23K26/1464 , B23K2101/001 , B33Y10/00 , B33Y40/00 , B33Y80/00
Abstract: There is disclosed a method of manufacturing a component. The method comprises generating, by additive manufacture, an intermediate structure comprising a core corresponding to the component, and one or more excess portions to be removed and comprises machining the intermediate structure to remove the excess portions. The core is generated by a first additive manufacturing procedure and the one or more excess portions are generated by a second additive manufacturing procedure. The second additive manufacturing procedure differs from the first additive manufacture so that the excess portions are fused at a higher rate than the core.
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Patent Agency Ranking
公开(公告)号：US20190233125A1
公开(公告)日：2019-08-01
申请号：US16239338
申请日：2019-01-03
Applicant: ROLLS-ROYCE plc
Inventor： Glenn A. KNIGHT , Richard SHARPE
CPC classification number: B64D13/04 , B64D13/02 , F01D15/10 , F02C7/26 , F02C7/32 , F04D25/06 , F05D2220/323 , F05D2220/76 , F05D2260/40311 , F16H1/28 , F16H3/08
Abstract: An aircraft cabin blower system includes a transmission configured to receive mechanical power from a gas turbine engine in the form of a first transmission input; and an electrical circuit including a first electrical machine, a second electrical machine, and power management system, wherein, when operating in a blower mode, the first electrical receives mechanical power from the gas turbine engine and act as a generator to provide electrical power to the power management system, and the second electrical machine acts as a motor providing mechanical power to the transmission in the form of a second transmission input, the second electrical machine being driven by electrical power from the power management system. The transmission's output drives a cabin blower compressor when operating in the blower mode, a speed of the output of the transmission being determined by a function of a speed of the first and second transmission inputs.
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公开(公告)号：US10364773B2
公开(公告)日：2019-07-30
申请号：US15298927
申请日：2016-10-20
Applicant: ROLLS-ROYCE plc
Inventor： Stephane M M Baralon
Abstract: A gas turbine engine comprising a fan, a bypass duct positioned downstream of the fan and defined by an inner casing and an outer casing, a series of outlet guide vanes arranged downstream of the fan, the outlet guide vanes extending between the inner casing and the outer casing of the bypass duct; and a bifurcation positioned downstream of the outlet guide vanes and extending between the inner casing and the outer casing. The bifurcation comprises a leading edge, and the leading edge of the bifurcation is shaped so as to protrude axially forward by a varying distance from the inner casing to the outer casing so as to improve uniformity of a static pressure field formed, in use, immediately upstream of the bifurcation.
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公开(公告)号：US10363603B2
公开(公告)日：2019-07-30
申请号：US15202066
申请日：2016-07-05
Applicant: ROLLS-ROYCE plc
Inventor： John H Boswell
IPC: B22F3/10 , B22F3/105 , B33Y10/00 , B28B1/00 , B29C64/153
Abstract: A powder deposition apparatus for producing a component comprises a base plate, an annular stack of heating elements, accommodating the base plate, one or more insulating elements, being interleaved between adjoining heating elements, a mechanism operable to deposit a plurality of layers of a powder material onto the base plate, and a laser energy source operable to selectively fuse a portion of the deposited layer. The annular stack of heating elements is sized such that a predetermined clearance is defined between the component and the annular stack of heating elements.As successive layers of the powder material are deposited onto the base plate, the base plate is lowered into the stack of heating elements, the heating elements being actuated sequentially to maintain a pre-determined temperature profile in the deposited layers.
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公开(公告)号：US10352187B2
公开(公告)日：2019-07-16
申请号：US15669358
申请日：2017-08-04
Applicant: ROLLS-ROYCE plc
Inventor： Michael P. Keenan
Abstract: A variable vane mechanism for adjusting the angle of stator vanes in a gas turbine engine is provided. The mechanism includes a circumferentially extending unison ring that is driven circumferentially around a casing by an actuator. The unison ring is connected to the stator vanes via levers such that the angle of the vanes changes with circumferential movement of the unison ring. The unison ring and the casing are each provided with at least one rigging hole in order to set the initial angle of the vanes. At least one of the unison ring and the casing are each provided with at least two rigging holes, so that the initial angle of the vanes can be adjusted by selecting different combinations of rigging holes. This may allow accumulations in tolerances to be compensated for and/or may allow the engine to be tested at different initial vane angles.
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公开(公告)号：US10344620B2
公开(公告)日：2019-07-09
申请号：US15645157
申请日：2017-07-10
Applicant: ROLLS-ROYCE PLC
Inventor： Mark J Simms , Edward J Smith
Abstract: An air cooled component for a turbine stage of a gas turbine engine, comprising: a main body having radially inner main gas path wall and a cooling chamber, the main gas path wall separating the main gas path of the turbine stage and the cooling chamber; at least one flange extending from the main body; a cooling cavity enclosed within the flange; and, an inlet conduit extending between and fluidically connecting the cavity and cooling chamber.
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