Patents Examined by Juan G Flores
  • Patent number: 10196911
    Abstract: A turbine engine assembly includes a first component, a second component and a third component arranged along an axis. The first component houses at least a portion of the third component. The assembly also includes a seal carrier, a seal land and a seal element, which seals a gap between the seal carrier and the seal land. The seal carrier is connected to the first component, and includes a groove surface and a groove. A first portion of the seal carrier seals a gap between a second portion of the seal carrier and the second component. The seal land is connected to the third component and includes a seal land surface. The seal element extends radially into the groove. The seal element is axially engaged with the groove surface and radially engaged with the seal land surface.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: February 5, 2019
    Assignee: United Technologioes Corporation
    Inventors: Decari S. Jenkins, Jorge I. Farah
  • Patent number: 10190571
    Abstract: The present disclosure is directed to a rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having a blade root section and a rigid ring insert. The rotor blade has pressure and suction sides extending between leading and trailing edges. The blade root section includes an end face configured to attach the rotor blade assembly to a hub. Further, the blade root section includes a span-wise end portion defined by inner and outer circumferential components separated by a radial gap. The radial gap includes a first laminate material embedded between the inner and outer circumferential components at a first span-wise depth and a second laminate material embedded between the inner and outer circumferential components at a second span-wise depth. Thus, the rigid ring insert is disposed in the radial gap and embedded between the first and second laminate materials.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: January 29, 2019
    Assignee: General Electric Company
    Inventors: Srikanth Samudrala, Biju Nanukuttan, Dhanesh Chandrashekar Pathuvoth, Willem Jan Bakhuis
  • Patent number: 10190428
    Abstract: A seal for a gas turbine engine includes a top, a bottom, a left side, a right side, a back and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side. The top includes a first vane mating surface and the bottom includes a second vane mating surface.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: January 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Bradley T. Duelm, Randall J. Brown, Nathan A. Shirk, Lewis M. Holby
  • Patent number: 10184344
    Abstract: Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band. The radially inner end of the nozzle vane is attached to the arcuate inner band through an interlocking transition zone including a plurality of projections alternately extending from the radially inner end of the nozzle vane and the arcuate inner band, respectively, to undetachably couple the nozzle vane and the arcuate inner band. Optionally, the radially outer end of each nozzle vane is also attached to the arcuate outer band through an interlocking transition zone.
    Type: Grant
    Filed: October 20, 2015
    Date of Patent: January 22, 2019
    Assignee: General Electric Company
    Inventors: Herbert Chidsey Roberts, Richard William Albrecht, Jr., Michael John McCarren, Peter Andrew Flynn, Michael Francis Xavier Gigliotti, Jr., Eric Alan Estill
  • Patent number: 10184343
    Abstract: A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: January 22, 2019
    Assignee: General Electric Company
    Inventors: Benjamin Paul Lacy, David Edward Schick, Sandip Dutta
  • Patent number: 10180127
    Abstract: The present invention relates to a wind turbine comprising a nacelle (1) installed on a tower (2) supported by a floating support. The nacelle is articulated with respect to the tower in a vertical plane, and it comprises means (12, 16) for correcting the nacelle tilt, means for automatically adjusting the correction means in accordance with sensors detecting the correction values, the adjustment means being synchronous with the movements of the floating support. Figure 4 to be published.
    Type: Grant
    Filed: December 14, 2011
    Date of Patent: January 15, 2019
    Assignee: IFP ENERGIES NOUVELLES
    Inventors: Christian Wittrisch, Pascal Longuemare
  • Patent number: 10156155
    Abstract: The present invention relates to a turbine engine having a casing (7) which has an inner wall (3i) forming a wall of an air duct (3) and at least one opening (7r) passing through the casing, leading into the duct (3) and forming a passage for an endoscope. The opening (7r) is closed during operation of the turbine engine by a stopper (8) which has an end-surface portion (8s) in the extension of the inner wall (3i). An indicator of wear to the inner wall of the casing is associated with the stopper (8) or with the inner wall (3i) of the casing, in the proximity of the stopper (8).
    Type: Grant
    Filed: May 13, 2014
    Date of Patent: December 18, 2018
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Sylvain Jacques Marie Gourdant, Laurent Jacquet, Philippe Nectoute
  • Patent number: 10150187
    Abstract: An airfoil (112) including an internal cooling circuit (136) to direct cooling fluid (120) through an interior of the airfoil. The airfoil also includes a trailing edge (114?) defining plugged holes (115) and cooling holes (116) along a radial direction (117). A selective group (314) of the cooling and plugged holes are based on a reduced cooling fluid requirement at the trailing edge (114?) resulting from an improved thermal barrier coating (126). A process (200) is also provided including removing (202) an airfoil from service in a gas turbine engine and adding or improving (204) a thermal barrier coating on the airfoil. The process also includes selectively (206) plugging holes in the airfoil in response to a reduced cooling fluid required through the airfoil as a result of the added or improved thermal barrier coating.
    Type: Grant
    Filed: July 26, 2013
    Date of Patent: December 11, 2018
    Assignee: Siemens Energy, Inc.
    Inventor: Bruce L. Smith
  • Patent number: 10145358
    Abstract: A wind turbine for converting wind into mechanical energy, includes a support and a vane rotatably connected to the support, the vane including a wind receptacle that can adopt a first configuration when the vane is in a position to travel in the direction of the wind, in which first configuration the receptacle has a first capacity to convert wind force into motion of the vane, and a second configuration when the vane is in a position to travel against the direction of the wind, in which second configuration the receptacle has a second capacity to convert wind force into motion of the vane, the second capacity being lower than the first capacity, wherein the turbine is provided with an arrangement that is operable to force the receptacle to adopt at least one of the configurations independent from the direction of the wind.
    Type: Grant
    Filed: July 3, 2013
    Date of Patent: December 4, 2018
    Inventor: Wilhelmus Helena Hendrikus Joosten
  • Patent number: 10145361
    Abstract: A wind turbine system is presented. The wind turbine system includes a wind turbine comprising a plurality of blades and a tower, and a processing subsystem configured to shut down the wind turbine by non-linearly pitching out the plurality of blades in the wind turbine towards a feather position at a pitch rate determined based upon a tower-fore-aft velocity of a top-portion of the tower during oscillations of the tower.
    Type: Grant
    Filed: November 25, 2013
    Date of Patent: December 4, 2018
    Assignee: General Electric Company
    Inventor: Pranav Agarwal
  • Patent number: 10132177
    Abstract: A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: November 20, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Fribourg, Pierre Delaleau, Florian Tellier
  • Patent number: 10132187
    Abstract: A clearance control assembly for a gas turbine engine includes a clearance control ring to position a blade outer air seal assembly radially relative to a blade tip. The clearance control ring is compression fit to the blade outer air seal assembly.
    Type: Grant
    Filed: August 7, 2014
    Date of Patent: November 20, 2018
    Assignee: United Technologies Corporation
    Inventors: Neil L. Tatman, Philip Robert Rioux
  • Patent number: 10113431
    Abstract: A fluidfoil is disclosed including a leading edge and a leading edge zone behind the leading edge. The leading edge zone extends spanwise for the full length of the fluidfoil. The leading edge zone includes one or more deflected regions which locally reduce the angle of attack of the fluidfoil.
    Type: Grant
    Filed: December 12, 2013
    Date of Patent: October 30, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Howoong Namgoong
  • Patent number: 10113481
    Abstract: A turbofan engine (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool includes a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: October 30, 2018
    Assignee: United Technologies Corporation
    Inventors: William G. Sheridan, Michael E. McCune
  • Patent number: 10107138
    Abstract: A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a first fluid flow device provided along an upper zone of the downstream guide vane so as to guide the fluid to the wall of the leading edge, and a second fluid flow device provided along a lower zone of the downstream guide vane so as to evacuate the fluid from the leading edge, wherein the first fluid flow device is arranged such that the wall of the leading edge is impacted by the fluid along a non-orthogonal direction.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: October 23, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Hélène Mazet, Morgan Balland, Jean-Yves Picart
  • Patent number: 10107103
    Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs.
    Type: Grant
    Filed: June 26, 2014
    Date of Patent: October 23, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Karin Costamagna, Karsten Kolk, Sebastian Stock, Vyacheslav Veitsman
  • Patent number: 10100642
    Abstract: A gas turbine engine having turbine discs includes a low diameter turbine rotor clamp for securing the turbine discs together. The rotor clamp includes a clamp sleeve, a clamp cylinder adapted to be threadably engaged to the clamp sleeve to apply an axial force on the turbine discs being coupled together. The rotor clamp includes an anti-score ring positioned between the bore of a turbine disc and the clamp cylinder and a lock tube used to prevent unwanted rotation of the clamp cylinder with respect to the clamp sleeve.
    Type: Grant
    Filed: August 31, 2015
    Date of Patent: October 16, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Daniel K. Morrison, Matthew P. Basiletti, Matthew I Jackson
  • Patent number: 10086933
    Abstract: Multiple motors may drive (rotate) a single shaft coupled to a propeller. The motors may be selected such that a first motor is capable of rotating the drive shaft in an event of a failure of a second motor coupled to the drive shaft. A one-way clutch bearing, or similar device, may interface between a motor and the drive shaft to enable free rotation of the drive shaft in an event of the motor becoming inoperable, such as the motor freezing or locking in a position due to failure caused by overheating or caused by other conditions or events. Use of the second motor may secure a position of the drive shaft which may support the propeller in radial eccentric loading.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: October 2, 2018
    Assignee: Amazon Technologies, Inc.
    Inventors: Nicholas Hampel Roberts, Dominic Timothy Shiosaki, Ricky Dean Welsh
  • Patent number: 10087948
    Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.
    Type: Grant
    Filed: March 30, 2015
    Date of Patent: October 2, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Lee Drozdenko, James O. Hansen, Christopher J. Hertel, Steven T. Holland
  • Patent number: 10081440
    Abstract: A ram air turbine actuator release device to release a ram air turbine actuator includes a lock bolt releasably engaged to the ram air turbine actuator, a toggle including a toggle roller to engage the lock bolt, and a toggle pivot to couple the toggle to the ram air turbine actuator, a toggle actuator, including an actuation source, and a stroke amplifier, including a piston coupled to the actuation source, a first hydraulic chamber having a first diameter in fluid communication with the piston, a second hydraulic chamber having a second diameter in fluid communication with the first hydraulic chamber, and a plunger in fluid communication with the second chamber, wherein a diameter ratio between the first hydraulic chamber and the second hydraulic chamber amplifies a displacement of the actuation source to displace the plunger to rotate the toggle to disengage the toggle roller from the lock bolt.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: September 25, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: David G. Bannon