Patents Assigned to Rolls-Royce Deutschland Ltd & Co KG
  • Publication number: 20200248335
    Abstract: An insert fixture has a base, a plurality of mounting brackets, and a plurality of separators. The plurality of separators extends vertically from the base and includes a plurality of grid portions extending the length of the insert fixture and a plurality of divider portions, which connect to the plurality of grid portions to form a plurality of individual component holders around one of the plurality of mounting brackets. Each individual component holder has two separated grid portion sections positioned on either side of the bracket. These grid portions have two divider portions which are also separated and positioned either side of the bracket at an angle relative to the two grid portions. The individual component holder forms a cell around the mounting bracket. The insert fixture may be constructed from a molybdenum alloy, lanthanum oxide and/or titanium zirconium molybdenum.
    Type: Application
    Filed: January 14, 2020
    Publication date: August 6, 2020
    Applicants: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Felix BIERNOT, Toma D. NIKOLOV, Priyesh R. PATEL, Justin P M TSANG
  • Patent number: 10731747
    Abstract: A gear device with a housing and a structural component rotatably mounted at the housing by a bearing that delimits a housing interior space. The gear device has a hydraulic fluid supply line for supplying hydraulic fluid into the interior space. A gap provides sealing between the housing and structural component. The gap is arranged radially between the housing and a further rotatable structural component or between a further housing and the structural component. A further bearing rotatably mounts the further structural component in the area of the housing or rotatably mounts the structural component at the further housing. An appliance couples the further structural component to the structural component or couples the housing to the further housing, and facilitates a relative movement between the further structural component and the structural component or between the housing and the further housing in the axial and/or radial directions.
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: August 4, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Stephan Uhkoetter, Stephane Prunera-Usach
  • Patent number: 10712006
    Abstract: A gas turbine combustion chamber includes first admixing air holes having first inner and outer center points, and second admixing air holes having second inner and outer center points. The first and second inner center points respectively lie on a side of the first and second admixing air holes oriented towards the combustion chamber. The first and second outer center points lie on a side of the first and second admixing air holes facing away from the combustion chamber. An equation L=D2/D1*(D2?D1)/C2 is fulfilled, with L being a distance between the first and second inner center points and/or the first and second outer center points; D1 and D2 being flow diameters of the first and second admixing air holes respectively at an entry and/or exit side to the combustion chamber and C being an average flow rate coefficient of the first and second admixing holes.
    Type: Grant
    Filed: October 5, 2017
    Date of Patent: July 14, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten Clemen, Torsten Voigt, Thomas Doerr
  • Publication number: 20200200036
    Abstract: A monitoring system for monitoring the axial position of a rotating shaft includes a phonic wheel which is mounted coaxially to the shaft for rotation therewith. The phonic wheel includes a circumferential row of teeth. The system further includes a sensor configured to detect the passage of the row of teeth by generating an alternating measurement signal. The teeth are configured around the row such that the teeth contribute a component to the alternating measurement signal. The teeth are tapered in an axial direction of the wheel and the sensor is positioned relative to the phonic wheel such that, in use, axial displacement of the shaft causes the signal generated by the sensor to vary either or both of the amplitude and the pulse width of the component, whereby the axial position of the shaft can be monitored.
    Type: Application
    Filed: November 21, 2019
    Publication date: June 25, 2020
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Björn PETERSEN, Peter HACKENBERG
  • Publication number: 20200200037
    Abstract: A gas turbine engine, and an aircraft including the gas turbine engine. The gas turbine engine comprising: an engine core comprising a turbine, a compressor, and a shaft system connecting the turbine to the compressor. The shaft system is axially located by a thrust bearing located forward of the turbine, and the engine is configured such that, in the event of a shaft break which divides the shaft system into a front portion located by the thrust bearing and a rear portion unlocated by the thrust bearing, the rear portion is free to move axially rearwardly under a gas load; and the engine further comprises an axial movement sensor configured to register a shaft break when it detects the axial movement of the rear portion of the shaft system.
    Type: Application
    Filed: November 22, 2019
    Publication date: June 25, 2020
    Applicants: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: David BROWN, Jorge CALDERON
  • Publication number: 20200191394
    Abstract: A fuel spray nozzle including a primary atomizer to discharge a flow of swirled atomised fuel along and around a fuel spray nozzle axis. The primary atomiser includes outer air swirler disposed radially outwardly of a fuel pre-filmer channel. A secondary atomiser disposed around the primary atomiser includes secondary inner air swirler to swirl flow along an inner air channel. The secondary inner air swirler disposed radially inwardly of a secondary fuel pre-filmer channel of the secondary atomiser. A primary outer air channel defined between the primary outer swirler and the secondary inner swirler. The secondary inner air swirler include splitter wall to separate swirling flow in the secondary inner channel from the primary flow of atomised fuel. The secondary inner air swirler includes primary cap wall integral with and extending radially inwardly from the splitter wall to direct flow from the primary outer channel inwardly towards the fuel spray.
    Type: Application
    Filed: November 20, 2019
    Publication date: June 18, 2020
    Applicants: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Luca TENTORIO, Juan Carlos ROMAN CASADO, Giacomo DI CHIARO, Jonathan KNAPTON, Filippo ZAMBON, Radu IRIMIA, Imon-Kalyan BAGCHI, James ROBINS, Tomasz STANKOWSKI
  • Patent number: 10677094
    Abstract: A transfer coupling includes a static component and a rotatable component arranged concentrically, the static component including a first number of radially extending ports and the rotatable component having a second number of radially extending ports the radially extending ports arranged in a common circumferential plane wherein the ports are configured and arranged, in use, to homogenise a flow area for a fluid being transferred through the ports and thereby create a homogenous volume flow.
    Type: Grant
    Filed: August 27, 2018
    Date of Patent: June 9, 2020
    Assignees: ROLLS-ROYCE PLC, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Stephan Uhkötter, Ulrich Adamczewski, Jack Francis Colebrooke
  • Patent number: 10670139
    Abstract: A planetary gear device for a turbomachine includes a planetary carrier and planetary wheel arranged in an axial direction between two planetary carrier areas connected to a support appliance, with the planetary wheel rotatably mounted on the support appliance. On outer sides facing away from the planetary wheel, the planetary carrier areas include cone surfaces that enclose connection areas with the support appliance, with diameters decreasing with increasing axial distance from the planetary wheel. Cone surfaces of a tensioning appliance radially enclose and are respectively adjusted thereto and act together such that a force that respectively results from an axial tensioning force of the tensioning appliance applied on the cone surfaces of the planetary carrier areas is applied at the connection areas between the support appliance and the planetary carrier areas. The tensioning appliance cone surfaces operatively connect via a coupling element.
    Type: Grant
    Filed: August 24, 2018
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Gideon Venter, Jan Schwarze
  • Patent number: 10669036
    Abstract: A turbofan engine including a core engine and at least one fan by means of which fluid is guided to a primary flow channel for the core engine as well as to a secondary flow channel of the turbofan engine, wherein the secondary flow channel is provided for an outer fluid flow that is guided past the core engine, and at least one splitter fairing arranged inside the secondary flow channel around which the fluid flow is flowing during operation of the turbofan engine, which cases at least one component of the turbofan engine that is guided radially through the secondary flow channel, and which has an end element with a leading edge section that is facing towards the fluid flow and/or a trailing edge section that is positioned in the flow direction of the fluid flow.
    Type: Grant
    Filed: August 9, 2017
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Robert Thies
  • Patent number: 10670270
    Abstract: A gas turbine combustion chamber with an inner combustion chamber wall and an outer combustion chamber wall, which form an annular combustor, is provided. Mixing air holes are formed in the inner combustion chamber wall and the outer combustion chamber wall in a circumferentially distributed manner. The respective combustion chamber wall is bulged in the area of the mixing air holes towards the interior space of the combustion chamber wall and the mixing air hole is arranged inside the bulge. The mixing air hole is formed at an inflow surface of the bulge with respect to the through-flow direction of the combustion chamber.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Carsten Clemen
  • Patent number: 10669937
    Abstract: A heat exchange system for a power gear box mechanically coupling at least low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Thierry Sibilli, Bjorn Ulrichsohn, Jonas Schwengler
  • Patent number: 10669949
    Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive train driven by a turbine, a driving side of the gearbox being driveably connected with a propulsive fan, is provided. The gas turbine includes at least one form locking connection device in a drive train enabling a controlled disengagement of at least one engine part from the drive train in case of a mechanical failure of the gas turbine engine or a part thereof and wherein the at least one form locking connection device is positioned in a torque carrying shaft or a torque carrying part of a shaft and/or wherein the at least one form locking connection device is positioned between the torque bearing coupling of the gearbox with the fan shaft and a torque carrier of the gearbox and at least one load stop for bearing an essential axial load.
    Type: Grant
    Filed: July 12, 2017
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dominic Boniface
  • Patent number: 10669886
    Abstract: A cooling device for cooling platforms of a guide vane ring of a gas turbine is arranged downstream inside a main flow channel of a combustion chamber. Cooling air passages are arranged in a wall of the platforms or of an intermediate piece that is connected therewith to guide cooling air for film cooling the surfaces of the platforms. At least in certain areas, the wall is configured with at least two layers having—as viewed from the main flow channel—an outer wall and a spaced apart inner wall forming a hollow space, wherein the hollow space can be impinged by cooling air through at least one cooling air blow-in opening inside the outer wall, and at least one cooling air blow-out opening is arranged inside the inner wall extending in the downstream direction to the surfaces of the platforms.
    Type: Grant
    Filed: March 16, 2017
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Knut Lehmann, Hamish Sweidan, Christian Kern
  • Patent number: 10655493
    Abstract: An arrangement for detecting a shaft break, including a shaft and a reference shaft that can be rotated together with the shaft, wherein an opening in the shaft overlaps with an opening in the reference shaft in an operational state of the shaft according to the intended use, and a signal conductor that can be severed extends through the two openings and is operatively connected to an evaluation unit, and the evaluation unit is configured to detect a severing of the signal conductor by applying a signal to the signal conductor to detect a shaft break of the shaft. The invention further relates to a turbomachine and a method.
    Type: Grant
    Filed: June 22, 2018
    Date of Patent: May 19, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Rudolf Lueck
  • Patent number: 10641127
    Abstract: A turbomachine with at least one rotatable shaft and at least one device for measuring a rotational movement of a rotatable structural component), in particular of the shaft, is provided. The device has a receiver and a first pattern carrier that has at least one pattern site. Here, the device comprises a second pattern carrier with at least one pattern site, wherein the pattern carriers are respectively connectable or connected to the rotatable structural component, so that they are rotatable together with the same about a rotational axis with respect to the receiver, namely in such a manner that the pattern site of the first pattern carrier is positioned in congruence with the pattern site of the second pattern carrier, and wherein the receiver is embodied and configured for detecting whether or not the pattern sites are positioned in congruence with one another.
    Type: Grant
    Filed: September 6, 2017
    Date of Patent: May 5, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Jens Kestering
  • Patent number: 10641107
    Abstract: A turbine blade has a root portion, a platform and an aerofoil, the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an axial chord length, the suction side wall defines part of the radially outward surface of the aerofoil, the suction side wall defines an overhang, the overhang has a maximum overhang length that is between 5% and 20% of the axial chord length of the blade and is located between 5% and 50% of the suction surface length from the leading edge.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: May 5, 2020
    Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: John David Coull, Nicholas Robert Atkins, Howard Peter Hodson, Adrian James White, Knut Lehmann, Manuel Herm
  • Patent number: 10634006
    Abstract: A guide vane of a gas turbine engine, in particular of an aircraft engine, which has a pressure-side wall, a suction-side wall, a guide vane root, a guide vane tip, a guide vane leading edge area that is impinged by a cooling air flow of a cooling system, a guide vane trailing edge area that is facing away from the guide vane leading edge area, and at least one channel for conducting a fluid to be cooled arranged in an internal space of the guide vane. At that, during operation of the gas turbine engine, a first part of the cooling air flow flows around a pressure-side wall, and a second part of the cooling air flow flows around the suction-side wall, and a third part of the cooling air flow flows through the internal space including the channel. What is further suggested is a gas turbine engine with at least one such static guide vane.
    Type: Grant
    Filed: June 28, 2016
    Date of Patent: April 28, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag Todorovic
  • Patent number: 10626925
    Abstract: A gas turbine engine with a geared turbofan arrangement with a gearbox in a drive shaft assembly driven by a turbine is provided. A driving side of the gearbox being driveably connected with at least one propulsive fan, with at least one mechanical fuse in the drive shaft assembly enabling a controlled disengagement of at least one engine part from the drive shaft assembly in case of a mechanical failure of the gas turbine engine or a part thereof and at least one load stop for bearing a load, in particular an axial or radial load in case of the mechanical failure of the gas turbine or a part thereof. A first mechanical fuse is positioned in a torque carrying shaft or a torque carrying part of a shaft, in particular in a torque bearing coupling between the shaft and the gearbox.
    Type: Grant
    Filed: September 18, 2017
    Date of Patent: April 21, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dominic Boniface
  • Patent number: 10619515
    Abstract: A structural component construction that is suitable and provided for the purpose of being further processed into a structural component of a gas turbine is provided. It is provided that the structural component construction has been manufactured by means of metal injection molding and subsequent sintering, and that it includes a support structure as an integral part of the structural component construction which is suitable for supporting the structural component during sintering, wherein the support structure is either not contained or not contained in its entirety in the finished structural component.
    Type: Grant
    Filed: May 27, 2016
    Date of Patent: April 14, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Roland Heinrich
  • Patent number: 10619490
    Abstract: A turbine rotor blade arrangement for a gas turbine, having a turbine disc and a turbine rotor blade ring that comprises a plurality of rotor blades. The turbine disc has disc channels for providing air, wherein a disc channel respectively ends in a discharge hole in the area of a blade root reception area. The rotor blades have cooling air channels for cooling the rotor blades. In the blade root or between the blade root and the blade root reception area, an air channel is formed via which sealing air is discharged that is fed in from the disc channel. It is provided that the blade root comprises a deflection device that is provided and is configured for the purpose of partially deflecting air exiting the disc channel in the direction of the air channel. Another embodiment of the invention relates to a method for the provision of sealing air in a turbine rotor blade arrangement.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: April 14, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Michael Friedrich, Sebastian Schrewe