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1
US10883373B2
Blade tip seal
Publication/Patent Number: US10883373B2 Publication Date: 2021-01-05 Application Number: 15/448,318 Filing Date: 2017-03-02 Inventor: Hall, Christopher   Krautheim, M. Stephen   Assignee: Rolls-Royce Corporation   IPC: F01D5/20 Abstract: A blade tip sealing portion forms the distal end of a rotor blade in a turbine engine to reduce or prevent leakage through the blade tip clearance. A rotor assembly comprises a casing, a rotor, and at least one rotor blade coupled to the rotor. The rotor blade comprises a root portion coupled to the rotor, a main airfoil body extending radially from the root portion, and a blade tip sealing portion. The blade tip sealing portion comprises a blade tip platform and a plurality of sealing members. The sealing members are positioned on the blade tip platform at an angle substantially perpendicular to an air flow across the blade tip platform and are spaced to effect overlap of adjacent sealing members in the direction of the air flow.
2
US10883379B2
Variable diffuser having a respective penny for each vane
Publication/Patent Number: US10883379B2 Publication Date: 2021-01-05 Application Number: 15/977,446 Filing Date: 2018-05-11 Inventor: Hall, Christopher   Knight, Glenn   Assignee: Rolls-Royce Corporation   IPC: F04D29/44 Abstract: A variable diffuser comprises a passage, at least two vanes disposed within the passage, and at least two pennies. The passage is defined between opposing disk faces of a hub and a tip. Each of the vanes comprises a body having a leading edge and a trailing edge. The body extends between the hub face and the disk face. Each of the pennies is coupled to a respective vane body near an edge of the penny and an actuator. Rotation of at least one penny changes the orientation of the respective vane relative to the hub face.
3
US2021003024A1
CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE
Publication/Patent Number: US2021003024A1 Publication Date: 2021-01-07 Application Number: 16/845,820 Filing Date: 2020-04-10 Inventor: Vetters, Daniel K.   Thomas, David J.   Freeman, Ted   Lamusga, Joseph   Uskert, Rick   Dierksmeier, Douglas D.   Shi, Jun   Engel, Todd   Brandt, Matt   Assignee: Rolls-Royce North American Technologies Inc.   Rolls-Royce Corporation   Rolls-Royce High Temperature Composites Inc.   IPC: F01D11/02 Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
4
US10662794B2
Strip seal axial assembly groove
Publication/Patent Number: US10662794B2 Publication Date: 2020-05-26 Application Number: 15/873,484 Filing Date: 2018-01-17 Inventor: Das, Sayon   Assignee: ROLLS-ROYCE CORPORATION   IPC: F01D11/00 Abstract: Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include blade track segments. The blade track segments may include a cavity formed at a circumferential end of the blade track segment. The blade track segments may further include an assembly groove configured to provide a clearance for axial insertion of an inter-segment strip seal. An inter-segment strip seal may be axially inserted past the assembly grooves and into the cavity. The inter-segment strip seal may cover a gap between adjacent blade track segments, thus blocking hot, high pressure fluid from contacting the turbine casing.
5
CA3020205A1
ANTI-ROTATION PIN AND SWAGED RING LOCK FOR A THREADED JOINT ON A STRUT
Publication/Patent Number: CA3020205A1 Publication Date: 2020-02-02 Application Number: 3020205 Filing Date: 2018-10-10 Inventor: Bell, Michael S.   Assignee: ROLLS-ROYCE CORPORATION   IPC: F16C7/00 Abstract: A strut and method for assembling a strut. The strut comprises two strut members attachable by a threading mechanism or the like. A first strut member is screwed into the second strut member. A pin hole is formed at the seam between the strut members and a pin is inserted into the pin hole. A locking ring is formed around the pin hole that includes an angular lip adjacent to the hole. The locking of the pin is accomplished, by swaging the angular lip into the hole and over the pin to lock the pin in the pin hole. The purpose of the pin is to ensure the joint does not untwist during operation.
6
US10648341B2
Airfoil leading edge impingement cooling
Publication/Patent Number: US10648341B2 Publication Date: 2020-05-12 Application Number: 15/352,020 Filing Date: 2016-11-15 Inventor: Barker, Brett J.   Rhodes, Jeffrey F.   Assignee: ROLLS-ROYCE CORPORATION   IPC: F01D5/18 Abstract: An airfoil including a spar and a cover sheet. Standoffs, a leading edge wall, and a separator wall extend away from an outer surface of the spar. The standoffs are arranged to define leading grooves disposed at the pressure side of the leading edge. The cover sheet is coupled to the leading edge wall and the standoffs over the leading grooves to define cooling passageways. The cooling passageways are in communication with one or more inlet ports formed in the spar, which are in communication with a plenum disposed within the spar. The cover sheet is arranged to define outlet ports or a slot in communication with the cooling passageway. Cooling air is delivered from the cooling air plenum through the inlet port for impingement cooling at the cover sheet, and traverses downstream through the cooling passageway to the outlet ports or slot for film cooling of the leading edge.
7
US10626731B2
Airfoil leading edge cooling channels
Publication/Patent Number: US10626731B2 Publication Date: 2020-04-21 Application Number: 16/580,784 Filing Date: 2019-09-24 Inventor: Barker, Brett   Varney, Bruce   Shoemaker, Brian   Bulgrin, Charles   Assignee: ROLLS-ROYCE CORPORATION   IPC: F01D5/00 Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.
8
US10549395B2
Hand tool for self aligned placement of surface mounted tooling element
Publication/Patent Number: US10549395B2 Publication Date: 2020-02-04 Application Number: 15/868,632 Filing Date: 2018-01-11 Inventor: Griffiths, George   Stewart, Andrew   Assignee: ROLLS-ROYCE CORPORATION   IPC: B23Q3/18 Abstract: A hand tool enabling self-aligned placement and post alignment clamping of a surface mounted tooling element and a method for manufacturing such a tool. Using an additive manufacturing process, a tool housing may be manufactured in which one or more internal voids allow insertion and rotational movement along and about a longitudinal axis of the housing, respectively, of a member having a radially extending portion. A handle and a brace may be coupled to the proximal and distal ends of the member to facilitate operation of the tool and placement of the surface mounted tooling element, respectively. Such member may also be spring loaded to enable the tool to clamp itself to a workpiece during the mounting operation, with the radially extending member portion limiting rotational travel of the brace.
9
US10551220B2
Capacitive measurement device
Publication/Patent Number: US10551220B2 Publication Date: 2020-02-04 Application Number: 15/194,080 Filing Date: 2016-06-27 Inventor: Fuller, Kenneth   Assignee: ROLLS-ROYCE CORPORATION   IPC: G01D5/24 Abstract: A capacitive measurement device for indicating when two surfaces moving relative to each other are spaced less than a predetermined distance apart. The device comprises a probe having an elongated conductor, an insulating core, a conducting inner guard, an insulating interlayer, and a conducting sheath. A portion of the conductor, insulating core and conducting inner guard form a probe tip which extends beyond the insulating interlayer and conducting sheath by a predetermined offset. The probe is configured to extend from a first surface by a predetermined distance and to generate a signal when the tip is contacted by a second surface.
10
US10774662B2
Separable turbine vane stage
Publication/Patent Number: US10774662B2 Publication Date: 2020-09-15 Application Number: 16/037,580 Filing Date: 2018-07-17 Inventor: Brown, Elise A. M.   Mitchell, Emma L.   Mcmillen, Elyse M.   Tondreau, Iii David L.   Koenig, Eric T.   Taketa, Linnea L.   Assignee: ROLLS-ROYCE CORPORATION   IPC: F01D17/16 Abstract: A vane stage segment is provided including an outer wall segment, an inner wall segment, and an airfoil. The outer wall segment is configured to be coupled to other outer wall segments to form an outer wall of the vane stage. The inner wall segment is spaced radially inward from the outer wall segment. At least one of the inner wall segment or the outer wall segment is separable between a forward portion and an aft portion. The airfoil extends between the outer wall segment and the inner wall segment.
11
US10639742B2
Vessel for joining materials
Publication/Patent Number: US10639742B2 Publication Date: 2020-05-05 Application Number: 15/013,489 Filing Date: 2016-02-02 Inventor: Shuck, Quinlan Yee   Nelson, Scott   Xu, Raymond   Assignee: ROLLS-ROYCE CORPORATION   IPC: B23K26/12 Abstract: A system and method for joining materials. The system includes a sealed chamber having a window. A laser is disposed external to the sealed chamber and heats objects in the sealed chamber through the window. The method includes sealing objects to be joined in the sealed chamber with a controlled environment and heating the objects with a laser disposed external to the sealed chamber.
12
US10619998B2
Method of measuring clearance between rotating and static components
Publication/Patent Number: US10619998B2 Publication Date: 2020-04-14 Application Number: 15/165,153 Filing Date: 2016-05-26 Inventor: Whitlock, Mark   Acker, Jonathan   Assignee: ROLLS-ROYCE CORPORATION   IPC: G01B11/14 Abstract: A method of measuring the clearance between a rotating component and a static component in a rotating machine. The method comprises installing a rub pin on an interior surface of the static component, operating the rotating machine such that the rotating component impinges on the rub pin, securing the rotating machine, and inserting an optical device to visually ascertain the length of rub pin remaining. The method reduces the time and cost of clearance determinations by avoiding disassembly or the degree of disassembly of the rotating machine required to conduct a clearance determination.
13
US2020200038A1
FAN CONTAINMENT ASSEMBLY HAVING A NESTING ACTIVITY
Publication/Patent Number: US2020200038A1 Publication Date: 2020-06-25 Application Number: 16/229,615 Filing Date: 2018-12-21 Inventor: Hall, Christopher   Kappes, Matthew   Patterson, Glenn   Heeter, Robert   Assignee: Rolls Royce Corporation   IPC: F01D21/04 Abstract: A containment assembly is disclosed for a turbofan engine. The containment assembly comprises a forward fence, an aft fence, a fan track liner, an intermediate casing member, an outer casing member, and an annular nesting cavity. The fan track liner is disposed axially between the forward and aft fences. The intermediate casing member is disposed radially outward of at least a portion of the fan track liner. The outer casing member is disposed radially outward of at least a portion of the intermediate member. The annular nesting cavity is bounded at least in part by the intermediate casing member and the outer casing member.
14
US10571415B2
Methods and apparatuses for evaluating ceramic matrix composite components
Publication/Patent Number: US10571415B2 Publication Date: 2020-02-25 Application Number: 15/652,910 Filing Date: 2017-07-18 Inventor: Shi, Jun   Assignee: ROLLS-ROYCE CORPORATION   IPC: G01N22/02 Abstract: Methods and apparatuses for evaluating ceramic matrix composite components are provided. In one example, a method for evaluating a ceramic matrix composite (CMC) component includes applying an electrical voltage to the CMC component at conditions to heat and cause a temperature increase in at least a portion of the CMC component. The temperature increase is sensed for detecting a presence of a defect in the CMC component.
15
US10527098B1
Systems and methods of oil distribution for a bearing
Publication/Patent Number: US10527098B1 Publication Date: 2020-01-07 Application Number: 16/146,494 Filing Date: 2018-09-28 Inventor: Lighty, Kerry   Schwendenmann, Andrew   Mcclellan, Eric   Assignee: ROLLS-ROYCE CORPORATION   IPC: F16C33/66 Abstract: Systems and methods are presented for directing oil to a bearing of a rotatable shaft. A system comprises a bearing race, a nozzle, and an oil catcher. The bearing race defines a first radial passage and a second radial passage axially displaced from the first radial passage. The nozzle is arranged to eject a stream of oil under pressure toward the shaft. The oil catcher is positioned between the bearing race and the shaft. The oil catcher comprises an annular catching flange at least partly defining a catchment region. The oil catcher defines a first channel extending from the catchment region to the first radial passage of the bearing race and a second channel extending from the catchment region to the second radial passage of the bearing race.
16
US10544866B2
Ceramic seal runner and mount for a rotating shaft
Publication/Patent Number: US10544866B2 Publication Date: 2020-01-28 Application Number: 16/240,912 Filing Date: 2019-01-07 Inventor: Fadgen, Daniel   Assignee: ROLLS-ROYCE CORPORATION   IPC: F16J15/3284 Abstract: A circumferential seal for a machine having a rotating shaft is provided. The seal may comprise a metallic mounting element and a ceramic sealing runner. The mounting element may be affixed around the shaft and comprise a base and a mounting member. The mounting member may extend radially outward from the base and axially along the shaft to form a radially inward facing cylindrical surface. The sealing runner may have a radially outward facing surface and be carried by said mounting element in axial and radial alignment by an interference fit between at least a portion of the radially outward facing surface of the runner and at least a portion of the radially inward facing surface of the mounting member.
17
US10533441B2
Floating interstage seal assembly
Publication/Patent Number: US10533441B2 Publication Date: 2020-01-14 Application Number: 15/611,992 Filing Date: 2017-06-02 Inventor: Sellhorn, James E.   Whitten, Michael   Assignee: ROLLS-ROYCE CORPORATION   IPC: F16J15/44 Abstract: A labyrinth seal system comprises a knife element and a stator element, the knife element having a plurality of teeth radially extending from a base and the stator element having a radially inner surface configured to interact with the plurality of teeth to create a seal. The knife element is axially constrained by and rotationally coupled to a turbine component, but has a degree of freedom in the radial direction with respect to that component.
18
US10566969B2
Analog power-up reset circuit for logic level reset
Publication/Patent Number: US10566969B2 Publication Date: 2020-02-18 Application Number: 16/025,468 Filing Date: 2018-07-02 Inventor: Costello, John Joseph   Assignee: ROLLS-ROYCE CORPORATION   IPC: H03K17/22 Abstract: An electrical reset circuit is configured to generate a reset pulse to reset one or more electrical components. The electrical reset circuit includes a first device electrically connected between a power supply input and a first node. The first device is configured to conduct current after the power supply input reaches a first voltage threshold. The electrical reset circuit also includes a second device electrically connected between the power supply input and a second node, where the second device is configured to conduct current after the power supply input reaches a second voltage threshold. In some examples, the electrical circuit includes a delay circuit configured to delay the reset pulse. Corresponding methods to providing a reset pulse are also contemplated.
19
US10731480B2
Varying seal rail fillet for turbine blades
Publication/Patent Number: US10731480B2 Publication Date: 2020-08-04 Application Number: 15/921,070 Filing Date: 2018-03-14 Inventor: Adavikolanu, Sivaram Surya Sanyasi   Puram, Gayathri   Assignee: ROLLS-ROYCE CORPORATION   IPC: F01D5/22 Abstract: A turbine blade assembly may be provided for use in a gas turbine engine. The turbine blade assembly may include an airfoil and a tip shroud. The airfoil may extend radially outward from an axis of rotation of the airfoil. The tip shroud may be located at a radial end of the airfoil. The tip shroud may include a seal rail that extends in a direction of rotation of the airfoil. A notch, including a Z-notch or a V-notch, may be situated on a first side of the seal rail at an end of the seal rail. A variable fillet may be situated on a second side of the seal rail that is opposite of the first side on which the notch is situated. The variable fillet is a fillet having a curvature that varies along a length of the second side.
20
US10738649B2
Reinforced oxide-oxide ceramic matrix composite (CMC) component and method of making a reinforced oxide-oxide CMC component
Publication/Patent Number: US10738649B2 Publication Date: 2020-08-11 Application Number: 15/667,995 Filing Date: 2017-08-03 Inventor: Clegg, Joseph   Assignee: ROLLS-ROYCE CORPORATION   IPC: F01D25/00 Abstract: A reinforced oxide-oxide CMC component for a gas turbine engine includes a composite body and a structural element embedded in the composite body, where the composite body comprises a 2D oxide-oxide composite and the structural element comprises a 3D oxide-oxide composite. The 2D oxide-oxide composite includes 2D woven or nonwoven oxide fibers in a first oxide matrix, and the 3D oxide-oxide composite includes 3D woven oxide fibers in a second oxide matrix. The first oxide matrix and the second oxide matrix may comprise the same or a different oxide.