公开(公告)号：US20190316488A1

公开(公告)日：2019-10-17

申请号：US16382923

申请日：2019-04-12

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Stefan MENCZYKALSKI ,  Stephan UHKOETTER ,  John R. MASON ,  David A. EDWARDS ,  Neil DAVIES ,  Lynn HAMMOND ,  David WILLIAMS

IPC: F01D25/20 ,  F02C7/36 ,  F02C7/06 ,  F02C7/14

Abstract: A gas turbine engine includes a gearbox receiving input from a core shaft and driving a fan at a lower speed than the core shaft. First and second oil circuits fluidly couple with an inlet and outlet of the gearbox. A third oil circuit fluidly couples with an inlet and outlet of the gearbox. The outlet of the gearbox includes a device directing oil from the gearbox to the first oil circuit, to the second oil circuit and to the third oil circuit when feeding to the gearbox exceeds a predefined oil flow rate, or deviates an operational value corresponding with that oil flow rate, and directs oil from the gearbox to the third oil circuit when feeding to the gearbox is the predefined flow rate or is a corresponding operational value or is greater than or equal to a further corresponding operational value.

公开(公告)号：US20170226859A1

公开(公告)日：2017-08-10

申请号：US15399457

申请日：2017-01-05

Applicant: ROLLS-ROYCE PLC

Inventor： David A. EDWARDS ,  Stewart T. THORNTON

IPC: F01D3/04 ,  F01D25/16

Abstract: A thrust balancing mechanism for balancing axial loads on a rotor thrust bearing 3 is described. The mechanism comprises a piston arrangement 6 axially mounted on a stationary structure 2, about a centre axis arranged, in use, in coaxial alignment with a rotating shaft 1 carrying the rotor thrust bearing 3. A hydrodynamic thrust bearing 8 is mounted, in use, between the piston 6 and the rotor thrust bearing 3. The piston 6 is pressurised so as to impart to the rotor thrust bearing 3, via the hydrodynamic thrust bearing 8, an axial load which counters an axial load imparted to the rotor thrust bearing 3 by the rotating shaft 1.

公开(公告)号：US20190309684A1

公开(公告)日：2019-10-10

申请号：US16357904

申请日：2019-03-19

Applicant: ROLLS-ROYCE plc

Inventor： David A. EDWARDS

IPC: F02C7/06 ,  F02C3/06 ,  F02C7/12

Abstract: A tank assembly (100) for a gas turbine engine is provided comprising a tank (102) and a plurality of restraints (112, 114). The restraints (112, 114) include a fixing part (124) for securing the tank (102) to a support structure (104). A first restraint (112) has a first rigidity in the direction of a length of the tank (102) and at least one second restraint (114) has a second rigidity in the direction of the length of the tank (102). Upon thermal expansion or contraction of the tank (102) relative to the support structure (104), the or each second restraint (114) flexes to a greater extent than the first restraint (112).

公开(公告)号：US20190078680A1

公开(公告)日：2019-03-14

申请号：US16059370

申请日：2018-08-09

Applicant: ROLLS-ROYCE plc

Inventor： David A. EDWARDS ,  David P. SCOTHERN

IPC: F16H57/04 ,  F16N25/04 ,  F16N7/36 ,  F16N7/16

Abstract: An auxiliary oil supply apparatus for a rotating device (50, 51), the rotating device comprising a primary oil supply (52), a rotating component (50) and a static component (51) situated radially outwardly of a centre of rotation of the rotating component (50) and arranged to collect oil (58) held radially outwardly from the rotating component (50) as the rotating component rotates. The auxiliary oil apparatus comprises a scoop (56) associated with the rotating component (50) and is responsive to a change in a known parameter to move between a first position in the static component (51) to a second position between the static component (51) and the centre of rotation.

公开(公告)号：US20200325827A1

公开(公告)日：2020-10-15

申请号：US16835674

申请日：2020-03-31

Applicant: ROLLS-ROYCE plc

Inventor： Clare L. BEWICK ,  David A. EDWARDS

IPC: F02C7/32 ,  F02C7/22

Abstract: The disclosure relates to a gas turbine engine (10) having an accessory gearbox assembly having an accessory gearbox (42). The accessory gearbox assembly is mounted adjacent a core (11) of the gas turbine engine (10) and has a support formation for supporting a conduit (50). The conduit (50) extends between a first location (52) on the engine (10) and a second location (54) on the engine (10). The first location (52) and the second location (54) may be spaced from the accessory gearbox (42) such that the conduit (50) does not operatively communicate with the accessory gearbox (42) in use. The accessory gearbox (42) may be axially mounted and may provide a bridge for supporting a plurality of conduits.

公开(公告)号：US20190316522A1

公开(公告)日：2019-10-17

申请号：US16382832

申请日：2019-04-12

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Stefan MENCZYKALSKI ,  Stephan UHKOETTER ,  John R. MASON ,  David A. EDWARDS ,  Neil DAVIES ,  Lynn HAMMOND ,  David WILLIAMS

IPC: F02C7/06 ,  F02C3/04

Abstract: A gas turbine engine for an aircraft including a unit supplied with oil from a first oil circuit and a second oil circuit. The first oil circuit and the second oil circuit each are fluidly coupled with at least one inlet and with at least one outlet of the unit and with at least one inlet and with at least one outlet of an oil tank. The first oil circuit and the second oil circuit are configured to receive oil from the oil tank and to direct the received oil to the unit. The oil tank is incorporating offset outlets to each of the oil circuits. The offset outlet of the second oil circuit is positioned higher in the oil tank than the offset outlet of the first oil circuit.

公开(公告)号：US20190218978A1

公开(公告)日：2019-07-18

申请号：US16233526

申请日：2018-12-27

Applicant: ROLLS-ROYCE plc

Inventor： David A. EDWARDS ,  Stewart T. THORNTON

IPC: F02C7/32 ,  F02C7/268 ,  F16H57/038

CPC classification number: F02C7/32 ,  F02C7/268 ,  F05D2220/50 ,  F05D2220/76 ,  F05D2260/4031 ,  F05D2260/53 ,  F05D2260/532 ,  F05D2260/85 ,  F16H57/038 ,  F16H2057/02026 ,  F16H2057/02039

Abstract: A gas turbine engine accessory gearbox assembly comprising an accessory gearbox and a plurality of accessories arranged to be driven by the accessory gearbox. The accessory gearbox comprises a gear train and an accessory gearbox casing enclosing the gears of the gear train. Each accessory is driven by a shaft and the shaft of each accessory has a spur gear. The gear train comprises the spur gears of the accessories. The shaft of at least one of the accessories has a bevel gear and the bevel gear is arranged to mesh with a further bevel gear and the further bevel gear is arranged to drive the accessory gearbox assembly. The accessories may be arranged in V-shape on the core engine casing within an aerodynamic core nacelle.

公开(公告)号：US20170356347A1

公开(公告)日：2017-12-14

申请号：US15600917

申请日：2017-05-22

Applicant: ROLLS-ROYCE plc

Inventor： David P. SCOTHERN ,  David A. EDWARDS

IPC: F02C7/32 ,  F16H1/22

CPC classification number: F02C7/32 ,  F02C7/06 ,  F05D2260/30 ,  F05D2260/4031 ,  F05D2260/96 ,  F16H1/22 ,  Y02T50/672

Abstract: A gas turbine engine accessory gearbox assembly has an accessory gearbox and a plurality of accessories arranged to be driven by the accessory gearbox. The accessory gearbox has a gear train and an accessory gearbox casing enclosing the gear train gears. Each accessory is driven by a drive shaft and the drive shafts of the accessories may be parallel. Each accessory has a first end and a second opposite end. Each accessory is secured at the first end to the accessory gearbox casing, a plurality of accessories are secured to a first side of the accessory gearbox casing and the second opposite end of at least two of the plurality of accessories are secured to a structural cross member. The structural cross member increases the stiffness and strength of the accessory gearbox assembly and allows the accessory gearbox casing to be reduced in thickness and reduces weight and cost.