公开(公告)号：US10485145B2

公开(公告)日：2019-11-19

申请号：US15285823

申请日：2016-10-05

Applicant: ROLLS-ROYCE plc

Inventor： John J A Cullen

IPC: H05K7/20 ,  H01B12/16 ,  H02G3/04 ,  H02G15/34

Abstract: This invention concerns a cryo-cooled electrical conduction network. The conduction network has an electrical network divided into two or more conductive sections, each section comprising electrical equipment (24, 28). The conductive network also has a coolant network for maintaining the temperature of a coolant in each section. The electrical equipment (24, 28) and a corresponding portion of the coolant network of each section is housed in a section enclosure (10, 12, 14). The coolant network includes a coolant interface (40) located between each section, wherein the coolant interface (40) is housed in an intermediate enclosure (16, 18, 20, 22) that is isolatable from the section enclosures (10, 12, 14) in the electrical conduction network.

公开(公告)号：US10472984B2

公开(公告)日：2019-11-12

申请号：US15680619

申请日：2017-08-18

Applicant: ROLLS-ROYCE PLC

Inventor： Andrew D Norton ,  Amir Rabani ,  States Chiwanga

IPC: F28D15/04 ,  F01D21/00 ,  G01N21/954 ,  G01M15/14

Abstract: Apparatus for insertion into a cavity of an object, the apparatus comprising: a first tube comprising a first end, a second end and a first cavity extending between the first end and the second; a member positioned within the first cavity of the first tube and configured to enable an action to be performed; a heat pipe including a first end, a second end, and a second cavity extending between the first end and the second end, the first tube being positioned within the second cavity of the heat pipe; and an actuator configured to move the first tube relative to the heat pipe.

公开(公告)号：US10472971B2

公开(公告)日：2019-11-12

申请号：US15232596

申请日：2016-08-09

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

Inventor： Adrian L Harding ,  Jens Taege

IPC: B22F3/15 ,  F01D5/14 ,  B22F3/105 ,  B28B1/00 ,  F01D25/00 ,  B22F5/04 ,  C04B35/645 ,  B29C64/153 ,  B29C64/40 ,  B22F5/00 ,  B24C1/10 ,  B33Y10/00

Abstract: A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and additional, sacrificial elements for supporting interim elements; b) on a base plate, depositing multiple layers of a powder including a material from which the pre-component will be manufactured; c) sintering the powder to form the pre-component to the defined geometry; d) removing at least some of the sacrificial elements from the pre-component; e) subjecting the remaining pre-component from step d) to a HIP step; and f) removing remaining sacrificial elements from the pre-component product of step e) to provide a component to the defined component geometry. In the definition of the pre-component geometry, the interim elements differ from the corresponding final shape elements in the defined component geometry such that during the HIP step, the interim shape elements adjust to form final shape elements in the defined component geometry.

公开(公告)号：US20190338674A1

公开(公告)日：2019-11-07

申请号：US16388380

申请日：2019-04-18

Applicant: Rolls-Royce plc

Inventor： David A. Edwards ,  Clare L. Bewick

IPC: F01D25/20 ,  F02K3/06 ,  F01M11/00 ,  F01M11/04 ,  B64D27/10

Abstract: An oil tank filling system for filling the oil tank of a gas turbine engine that includes an aft core cowl. The system includes: an oil tank that is located within a core of the engine; an oil access port located on the aft core cowl; an oil tank filling pipe that connects the oil access port to a tank filling port on the oil tank; and a hydraulic lock that prevents oil entering the oil tank once the oil tank contains a predetermined volume of oil. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.

公开(公告)号：US20190338672A1

公开(公告)日：2019-11-07

申请号：US16387953

申请日：2019-04-18

Applicant: Rolls-Royce plc

Inventor： Samuel W. White ,  William A. Malewicz ,  Sebastian Ray ,  Cristina Diaz Garcia ,  David A. Edwards

IPC: F01D25/20 ,  F02C7/06 ,  F02C3/04 ,  F02K3/06

Abstract: An oil tank filling system for filling the oil tank of a gas turbine engine. The system includes an oil tank located within a core of the engine, an oil filling reservoir located within a bifurcation that extends from the core of the engine, an oil tank filling pipe that leads from the oil filling reservoir to a tank filling port on the oil tank, and an oil pump. The system is configured so that the oil pump pumps oil from the oil filling reservoir through the oil tank filling pipe and the tank filling port to fill the oil tank. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.

公开(公告)号：US20190338669A1

公开(公告)日：2019-11-07

申请号：US16387836

申请日：2019-04-18

Applicant: Rolls-Royce plc

Inventor： Samuel W. White ,  William A. Malewicz ,  Sebastian Ray ,  Cristina Diaz Garcia

IPC: F01D25/18 ,  F16N19/00

Abstract: An oil tank filling system for filling the oil tank of a gas turbine engine. The system includes an oil tank located within the core of the engine, an engine oil filling port located on a bifurcation below the core of the engine, and an oil tank filling pipe that leads from the engine oil filling port to a tank filling port on the oil tank. The engine oil filling port is detachably connectable to an off-engine oil pump that when connected to the engine oil filling port and supplied with oil pumps oil into the engine oil filling port and through the oil tank filling pipe to the tank filling port to fill the oil tank. A method of filling the oil tank of a gas turbine engine and a gas turbine engine that includes the oil tank filling system are also disclosed.

公开(公告)号：US20190337246A1

公开(公告)日：2019-11-07

申请号：US16387107

申请日：2019-04-17

Applicant: Rolls-Royce plc

Inventor： Alexis LAMBOURNE ,  Alexander C. SMITH ,  Jameel B. KHAN

IPC: B29C73/10 ,  B29C73/32 ,  B29C35/08 ,  B29C35/02 ,  C08J5/04

Abstract: A procedure for repairing a polymer matrix composite component is provided. The procedure includes the steps of: providing a polymer matrix composite component having a site prepared for repair by removal of damaged or defective material; locating an uncured, polymer matrix composite repair patch at the site to re-build the component thereat; and curing the polymer matrix of the repair patch by heating the patch using eddy currents induced by one or more alternating current coils. The repair patch is without metallic additives, such that the repaired polymer matrix composite after the curing step is also without metallic additives in the vicinity of the repair patch.

公开(公告)号：US10465532B2

公开(公告)日：2019-11-05

申请号：US15855594

申请日：2017-12-27

Applicant: ROLLS-ROYCE PLC

Inventor： Bogachan Alpan

IPC: B22C9/04 ,  B22C9/10 ,  B22C21/14 ,  B22C7/02 ,  F01D5/28 ,  F01D25/00

Abstract: A method locates and maintains a core in fixed space relationship within the interior of a shell mould. The method provides at least one pin extending into the core with at least one axial end of the pin protruding from the core. A wax pattern having an outer surface is formed by encasing the core and at least one protruding axial end of the pin in wax such that at least one protruding axial end of the pin terminates at the outer surface of the wax pattern. A shell mould is formed around the wax pattern such that, upon removal of the wax pattern, and in a subsequent casting process for production of hollow metal components, at least one protruding axial end of the pin abuts the shell mould, thus fixing the pin and maintaining a position of the core relative to the mould. The protruding axial end of the pin has an enlarged head.

公开(公告)号：US20190330988A1

公开(公告)日：2019-10-31

申请号：US16379925

申请日：2019-04-10

Applicant: ROLLS-ROYCE plc

Inventor： Steven HILLIER

IPC: F01D5/18 ,  F01D5/28 ,  F01D25/12 ,  B28B23/00

Abstract: The disclosure relates to a ceramic matrix composite (CMC) aerofoil. Example embodiments include an aerofoil comprising first and second tubular CMC cores (302, 303) extending along a longitudinal axis of the aerofoil; and an outer CMC layer surrounding the first and second tubular CMC cores (302, 303) and defining an outer shape of the aerofoil having leading and trailing edges, wherein fibres within a wall of the second tubular CMC core extend to the trailing edge of the aerofoil.

公开(公告)号：US10458274B2

公开(公告)日：2019-10-29

申请号：US15625523

申请日：2017-06-16

Applicant: ROLLS-ROYCE plc

Inventor： Phillip J Doorbar ,  Jason J Madge

IPC: F01D25/00 ,  F01D15/12 ,  F01D5/06 ,  F01D15/08 ,  F01D25/16 ,  F16H1/28 ,  F16H57/08 ,  F02C7/36

Abstract: A gas turbine engine comprises a gearbox comprises a sun gear, an annulus gear, a plurality of planet gears and a carrier. The sun gear meshes with the planet gears and the planet gears mesh with the annulus gear. The planet gear carrier comprising a first ring, a second ring spaced axially from the first ring and a plurality of circumferentially spaced axles extending axially between the first ring and the second ring. Each planet gear is rotatably mounted on a respective one of the axles and the axles are arranged at a first radius. At least one of the first ring and the second ring comprises a metal matrix composite material ring and the metal matrix composite ring comprises a ring of reinforcing fibres and the ring of reinforcing fibres having a second radius greater than the first radius.