Specific Casing Or Vane Material Patents (Class 415/200)
  • Patent number: 11434177
    Abstract: A component for use in a gas turbine engine is made from ceramic materials. The component is made from a core preform containing ceramic reinforcement fibers. A plurality of preform tows are applied on at least a portion of the core preform and extend along at least a portion of the core preform to provide an outermost surface. The core preform and the plurality of preform tows are infiltrated with ceramic matrix material to form a ceramic matrix composite component.
    Type: Grant
    Filed: May 13, 2019
    Date of Patent: September 6, 2022
    Inventors: Anthony G. Razzell, Michael J. Whittle, Ian M. Edmonds
  • Patent number: 11428114
    Abstract: A lever for a VTG guide vane arrangement of a radial turbine with a main body with a fork-shaped coupling section with two limbs. A wear-resistant contact block is arranged on an inner side of at least one of the limbs. The wear-resistant contact block is designed for operative engagement with an adjusting ring of the VTG guide van arrangement, giving rise to the effect of increased wear resistance at least in the region of the engagement with the VTG guide vane arrangement. Furthermore, a VTG guide vane arrangement having such a lever, a radial turbine having such a VTG guide vane arrangement, and a supercharging device having such a radial turbine.
    Type: Grant
    Filed: December 6, 2021
    Date of Patent: August 30, 2022
    Assignee: BorgWarner Inc.
    Inventors: Nico Kanoffsky, Thomas Ramb
  • Patent number: 11415013
    Abstract: An integral, one-piece ceramic matrix composite turbine vane adapted for use in a gas turbine engine includes an airfoil and two platforms. The airfoil extends radially relative to an axis of the gas turbine engine between the first platform and the second platform. The platforms extend circumferentially partway about the axis of the gas turbine engine.
    Type: Grant
    Filed: September 30, 2021
    Date of Patent: August 16, 2022
    Inventors: Michael J. Whittle, Laurie Bootle
  • Patent number: 11408334
    Abstract: Methods and systems are provided for a turbocharger system. In one example, a system comprises an actuator configured to adjust a position of a plurality of guide vanes and a position of a coolant valve configured to adjust coolant flow through a turbine coolant jacket or a compressor coolant jacket.
    Type: Grant
    Filed: December 2, 2020
    Date of Patent: August 9, 2022
    Assignee: Ford Global Technologies, LLC
    Inventors: Franz J. Brinkmann, Ludwig Stump, Carsten Weber, Stefan Quiring, Kai Kuhlbach, Jan Mehring
  • Patent number: 11353031
    Abstract: A series fan includes a first fan and a second fan. The first fan includes a first frame body with a wind incoming side and a connection side at two sides, a first dynamic blade impeller and a first shaft seat. The first dynamic blade impeller is pivotally disposed on the first shaft seat and has first dynamic blades. The second fan includes a second frame body, a second dynamic blade impeller and a second shaft seat. Two sides of the second frame body are formed with a wind outgoing side and a mating side mated with the connection side in communication therewith. The second dynamic blade impeller is pivotally disposed on the second shaft seat and has second dynamic blades. At least one connected section of the second dynamic blade is integrally connected with at least one connection section of the first dynamic blade to form a driving blade.
    Type: Grant
    Filed: June 29, 2021
    Date of Patent: June 7, 2022
    Assignee: Asia Vital Components Co., Ltd.
    Inventor: Chu-Hsien Chou
  • Patent number: 11338400
    Abstract: A method of manufacturing a compressor stator having: a first stator blade with a first leading edge and a first trailing edge; a second stator blade disposed a circumferential distance from the first stator blade, the second stator blade having a second leading edge disposed an axial distance from the first leading edge and a second trailing edge disposed an axial distance from the first trailing edge; the method comprising: using additive manufacturing to deposit and fuse together progressive layers of metal material commencing at a substrate to form the first stator blade, the second stator blade, at least one intermediate support structure disposed between the first stator blade and the second stator blade, and at least one primary support structure disposed between the substrate and at least one of: the first stator blade; and the second stator blade; and removing the primary support structure and the intermediate support structure.
    Type: Grant
    Filed: May 12, 2021
    Date of Patent: May 24, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ian A. MacFarlane, Peter Townsend, Hong Yu
  • Patent number: 11319879
    Abstract: There is provided a manufacturing method of a turbine casing capable of easily realizing improvement of reliability. A manufacturing method of a turbine casing according to an embodiment is a manufacturing method of a turbine casing which includes an outer casing formed of ferritic heat resistant steel and an inner casing disposed inside the outer casing and formed of austenitic heat resistant steel, and in which an exhaust hood to which a working medium after performing work in turbine stages is exhausted, is covered by the inner casing. Here, the inner casing is manufactured by using members produced by at least either forging or rolling.
    Type: Grant
    Filed: December 13, 2019
    Date of Patent: May 3, 2022
    Assignee: TOSHIBA ENERGY SYSTEMS & SOLUTIONS CORPORATION
    Inventors: Shogo Iwai, Tsuguhisa Tashima, Toshio Morimoto
  • Patent number: 11306598
    Abstract: The invention relates to a method of fabricating a turbine engine blade out of composite material comprising fiber reinforcement densified by a matrix, the blade comprising an airfoil, a platform situated at a longitudinal end of the airfoil, and at least one functional element projecting from the outside face of the platform. The method comprises: making a single-piece fiber blank by multilayer weaving; shaping the fiber blank to obtain a single-piece fiber preform having a first portion (302) forming a preform for the blade airfoil (320) and a second portion (314) forming a preform for the platform (340) and at least one preform for a functional element (352; 354); and densifying the fiber preform with a matrix. The second preform portion comprises a set of yarn layers interlinked by weaving with at least one zone of non-interlinking being provided to make it possible to deploy the functional element preform relative to the first platform preform.
    Type: Grant
    Filed: November 7, 2019
    Date of Patent: April 19, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Roussille, Jéremy Blachier, Marie Lefebvre
  • Patent number: 11306608
    Abstract: A gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: April 19, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Sébastien Marin, Quentin Damien Lombart
  • Patent number: 11286810
    Abstract: An outflow housing for a turbine section of a steam turbine. The outflow housing has an outflow housing wall, which surrounds a central drum chamber along a housing longitudinal axis, and a connection interface for connecting the outflow housing to a turbine housing of the steam turbine. A sealing device for sealing an end of the outflow housing, which end is arranged at the rear in the flow direction, with respect to a turbine shaft of the steam turbine is arranged on the outflow housing wall, wherein the sealing device is sealed to the outflow housing wall. A steam turbine has the outflow housing herein.
    Type: Grant
    Filed: July 4, 2017
    Date of Patent: March 29, 2022
    Assignee: Siemens Energy Global GmbH & Co. KG
    Inventors: Robert Hilleke, Stefan Preibisch
  • Patent number: 11255341
    Abstract: A centrifugal fan impeller structure includes a hub and multiple blades extending from an outer circumference of the hub. Each blade has a fixed end, a free end, an upper end face, a lower end face, a front end face and a rear end face. The front and rear end faces define therebetween a thickness. The thickness ranges from 0.05 mm to 0.15 mm. The are two inclinations between the upper and lower end faces of the blade, whereby the thickness of the blade is minified to increase the number of the blades. By means of the inclinations, the blades are not subject to breakage in the demolding process.
    Type: Grant
    Filed: September 18, 2020
    Date of Patent: February 22, 2022
    Assignee: Asia Vital Components Co., Ltd.
    Inventor: Min-Sheng Cheng
  • Patent number: 11162377
    Abstract: A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.
    Type: Grant
    Filed: May 31, 2019
    Date of Patent: November 2, 2021
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce North American Technologies Inc.
    Inventors: Robert J. Shinavski, Thomas Tran, Kevin Lukhard, Ted J. Freeman, Steffan Brown
  • Patent number: 11156126
    Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: October 26, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Colin J. Kling, Darin S. Lussier
  • Patent number: 11131309
    Abstract: A molten metal pump includes an impeller, a pump base housing at least partially enclosing the impeller, a shaft connected to the impeller, a motor connected to the shaft, a motor mount plate for supporting the motor; and a post for connecting the motor mount plate to the pump base housing. The molten metal pump can include a connector that connects the post to the motor mount plate. The molten metal pump can include a socket for connecting the shaft to the motor. The shaft can comprise an assembly including an elongated metal rod having a first end and a second end and a metal non-circular drive member attached at the second end of the elongated metal rod.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: September 28, 2021
    Assignee: PYROTEK, INC.
    Inventors: Jorge A. Morando, Jon Tipton, George S. Mordue, Mark Bright, Lennard Lutes, Richard S. Henderson, Chris T. Vild
  • Patent number: 11085327
    Abstract: A bearing section for an exhaust turbocharger comprises a receiving opening for receiving a shaft of a rotor assembly of the exhaust turbocharger. The bearing section is designed for positioning bearing elements for supporting the shaft. A lubricant circuit is designed for supplying lubricant to the bearing elements. Lubricant channels are formed in the bearing section. In order to reduce a component temperature of the bearing section, a cooling jacket is provided, through which coolant can flow. The cooling jacket comprises a coolant channel, an inlet channel and an outlet channel. The inlet channel issues at a first opening point into the coolant channel and the outlet channel is connected at a second opening point to the coolant channel in such a way that a flow can pass therethrough. A rib is provided in the coolant channel.
    Type: Grant
    Filed: March 29, 2018
    Date of Patent: August 10, 2021
    Assignee: IHI Charging Systems International GmbH
    Inventor: Gerhard Jungmann
  • Patent number: 11073103
    Abstract: An exhaust mixer arrangement for a gas turbine engine comprises an exhaust cone, a lobed exhaust mixer surrounding at least a portion of the exhaust cone and a cover mounted to an outer surface of the exhaust cone. The cover and the outer surface of the exhaust cone define a dead-end cavity for receiving a stiffener ring. A plurality of circumferentially spaced-apart struts interconnect at least a number of lobes of the lobed exhaust mixer to the stiffener ring.
    Type: Grant
    Filed: January 17, 2019
    Date of Patent: July 27, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Philippe Boyer, Daniel Coutu
  • Patent number: 11053799
    Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: July 6, 2021
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Mageshwaran Ramesh, Thomas Schreier, Ingo Kuehn, Gregoire Etienne Witz
  • Patent number: 11047301
    Abstract: A highly efficient gas turbine engine includes the fan of the gas turbine engine driven from a turbine via a gearbox, such that the fan has a lower rotational speed than the driving turbine, thereby providing efficiency gains. The efficient fan system is mated to a core that has low cooling flow requirements and/or high temperature capability, and which may have particularly low mass for a given power.
    Type: Grant
    Filed: May 14, 2019
    Date of Patent: June 29, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventors: Pascal Dunning, Michael J Whittle, Roderick M Townes
  • Patent number: 11009044
    Abstract: An outlet port part has a heat insulating portion for preventing heat obtained from a heater disposed in the outlet port part from being transmitted toward a base side, and for transmitting the heat efficiently to the back (the vacuum pump side) of the outlet port. The heat insulating portion of the outlet port part is provided with a flange portion formed on the outer peripheral surface of the outlet port part, and a heat insulating spacer disposed in close contact with the flange portion. Alternatively, an outlet port part flange portion that is configured by integrating the flange portion formed on the outer peripheral surface of the outlet port part and the foregoing heat insulating spacer functions as the heat insulating portion. This configuration can efficiently increase the temperature of the entire outlet port of the vacuum pump, thereby reducing the amount of product and deposit.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: May 18, 2021
    Assignee: Edwards Japan Limited
    Inventors: Yoshiyuki Sakaguchi, Norihiro Kurokawa
  • Patent number: 10982311
    Abstract: A design method of tangential gradient thermal spraying coating for complex profile workpieces solves the erosion-resistant problem, and obtains a corresponding relation between the ductile-brittle ratio of the thermal sprayed coating and the impact angle change. The method includes: determining the complex profile part surface impact angle change rule according to the part operation environment conditions; selecting an erosion-resistant coating material according to the service condition requirement; obtaining the relation among the impact angle, ductile-brittle angle and erosion rate of the coating by an erosion test; determining the coating and the impact angle ductile-brittle corresponding relation curve; and performing spraying by using dual-channel powder feeding thermal spraying equipment the powder feeding quantity of which is adjustable in real time, based on a matching relation between the tangential gradient coating and the surface impact angle.
    Type: Grant
    Filed: September 30, 2018
    Date of Patent: April 20, 2021
    Assignee: SHANDONG UNIVERSITY
    Inventors: Fangyi Li, Haiyang Lu, Zhen Li, Jiyu Du, Jiantong Shang, Jianfeng Li, Liming Wang, Yanle Li, Ziwu Liu, Xingyi Zhang, Xueju Ran
  • Patent number: 10900364
    Abstract: A stator vane assembly for a gas turbine engine includes an inner vane support defining a first aperture, an outer vane support defining a second aperture, a stator having an inner end that extends through the first aperture and an outer end that extends through the second aperture, and a first bracket. The first bracket is operatively connected to the inner vane support and extends over the first aperture. The first bracket and the inner vane support defining a first pocket.
    Type: Grant
    Filed: July 12, 2017
    Date of Patent: January 26, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William R. Edwards, Nicholas Hunnewell
  • Patent number: 10821681
    Abstract: Methods for preparing ceramic products using liquid infusion technology and products formed from the same are provided. The methods and products include the incorporation of a particulate material and binder between ceramic fibers such that the fibers may be properly spaced during formation of the ceramic product. Ceramic matrix composite products can thereby be provided using near net shaping methods.
    Type: Grant
    Filed: January 20, 2017
    Date of Patent: November 3, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jared Hogg Weaver, Nathan Carl Sizemore
  • Patent number: 10808562
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a housing mountable to an engine static structure, a seal carrier secured to the housing and configured to be selectively biased from the housing, and a wedge seal secured to the seal carrier. The wedge seal abuts against sealing surfaces of adjacent blade outer air seals in response to movement of the seal carrier relative to the housing. The wedge seal is separate and distinct from the seal carrier. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
    Type: Grant
    Filed: January 23, 2019
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10724122
    Abstract: An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.
    Type: Grant
    Filed: March 10, 2017
    Date of Patent: July 28, 2020
    Assignee: NUOVO PIGNONE TECNOLOGIE SRL
    Inventors: Antonella Dimatteo, Iacopo Giovannetti
  • Patent number: 10711635
    Abstract: An apparatus and method for a multiple layer fan casing surrounding a fan having a plurality of circumferentially spaced blades rotatable about a rotational axis and having a sub-portion defining a blade impact zone, the multiple layers comprising an inner fiber layer confronting the blades, an outer fiber layer overlying the inner carbon layer, a glass layer sandwiched between the inner and outer composite fiber layers.
    Type: Grant
    Filed: November 7, 2017
    Date of Patent: July 14, 2020
    Assignee: General Electric Company
    Inventors: Frank Worthoff, Benjamin James Roby, Scott Roger Finn
  • Patent number: 10696424
    Abstract: Functional components of spacecraft structures can be subject to detrimental impacts by energetic particles produced from an electric propulsion system. A graphene coating applied to a functional component can maintain electrical conductivity upon a surface of the functional component, thereby allowing charge dissipation to take place, while also resisting sputtering erosion resulting from impacts of the energetic particles. Accordingly, spacecraft structures can include an electric propulsion system, a functional component that is at least partially impacted by an outflow of the electric propulsion system, and a graphene coating upon the functional component. Methods for operating such spacecraft structures can include generating an outflow of energetic particles from an electric propulsion system of a spacecraft structure, and at least partially impacting the outflow of energetic particles upon a functional component of the spacecraft structure, where the functional component has a graphene coating thereon.
    Type: Grant
    Filed: June 29, 2016
    Date of Patent: June 30, 2020
    Assignee: LOCKHEED MARTIN CORPORATION
    Inventors: Vadim Khayms, Steven W. Sinton, Peter V. Bedworth
  • Patent number: 10697470
    Abstract: A containment case includes a fan assembly including a hub having a plurality of fan blades extending radially outward between radially inward blade roots and radially outward blade tips. Containment case includes a radially outer shell circumscribing fan assembly and having a first radially inner surface and a radially outer surface, an inner structure having a second radially inner surface extending along first radially inner surface, and a trench extending circumferentially along second radially inner surface into inner structure from second radially inner surface. The trench is approximately axially aligned with the fan assembly. The containment case also includes, within the trench, a trench filler layer configured to dissipate impact energy from a released fan blade and having a plurality of sheets including a fibrous composite material having a plurality of fibers fabricated within each sheet, where the sheets are coupled together into a repeating pattern of hollow units.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: June 30, 2020
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Douglas Duane Ward
  • Patent number: 10655500
    Abstract: A fan containment case for a gas turbine engine is provided which includes a barrel having an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion. The outermost portion has an outermost band of material made of carbon fiber composite and the innermost portion has an innermost band of material made of carbon fiber composite. The interior portion includes a first interior band and a second interior band adjacent the first interior band. The first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second interior band is made of an aramid material. The innermost portion has an innermost band of material made of carbon fiber composite.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: May 19, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Robert W. Heeter
  • Patent number: 10641287
    Abstract: According to one aspect, a fan containment case for a gas turbine engine is provided which includes a barrel having a first band of material on an outside of the barrel. The first band is made of carbon fiber composite. The barrel further includes a second band of material inboard of the fan case and made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite. The barrel also includes a third band of material made of carbon fiber composite inboard of the second band.
    Type: Grant
    Filed: September 6, 2016
    Date of Patent: May 5, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Matthew J. Kappes, Robert W. Heeter, Benedict N. Hodgson
  • Patent number: 10626882
    Abstract: A centrifugal fan with an increased shutoff pressure maintains a negative pressure between a casing and a rotatable disk. The centrifugal fan includes an impeller including a rotatable disk and blades extending vertically from the rotatable disk and arranged radially about an axis of rotation of the rotatable disk toward a rim of the disk, a casing accommodating the impeller and including a base plate at its end face nearer the rotatable disk, and a motor mounted on the base plate externally and including a shaft fixed at a center of the rotatable disk to rotate the impeller. The rotatable disk has reflux holes at positions between inner rims and outer rims of the blades in its radial direction. The reflux holes allow a gas to reflux from between the rotating disk and the base plate inside the impeller as the impeller rotates.
    Type: Grant
    Filed: July 23, 2018
    Date of Patent: April 21, 2020
    Assignee: Rinnai Corporation
    Inventor: Tatsuyoshi Nakatani
  • Patent number: 10562097
    Abstract: The invention relates to systems for transferring molten metal from one structure to another. Aspects of the invention include a transfer chamber constructed inside of or next to a vessel used to retain molten metal. The transfer chamber is in fluid communication with the vessel so molten metal from the vessel can enter the transfer chamber. A powered device, which may be inside of the transfer chamber, moves molten metal upward and out of the transfer chamber and preferably into a structure outside of the vessel, such as another vessel or a launder.
    Type: Grant
    Filed: December 20, 2017
    Date of Patent: February 18, 2020
    Assignee: Molten Metal Equipment Innovations, LLC
    Inventors: Paul V. Cooper, Vincent D. Fontana
  • Patent number: 10539974
    Abstract: In a casing for an electronic apparatus, a plurality of ribs are integrally formed on an inner surface of the casing, and the plurality of ribs form an isogrid structure in which a plurality of equilateral-triangular segments are arranged regularly adjacent to each other.
    Type: Grant
    Filed: October 3, 2018
    Date of Patent: January 21, 2020
    Assignee: PANASONIC INTELLECTUAL PROPERTY MANAGEMENT CO., LTD.
    Inventor: Tetsuya Urimoto
  • Patent number: 10533424
    Abstract: A rotor for a gas turbine engine includes a hub having an outer periphery, a first plurality of blades arranged on the outer periphery of the hub, and a second plurality of blades arranged on the outer periphery of the hub. The first plurality of blades is made of a first material and has a first elastic modulus over density ratio. The first plurality of blades has a first natural frequency. The second plurality of blades is made of a second material and has a second elastic modulus over density ratio. The second elastic modulus over density ratio is different from the first elastic modulus over density ratio. The second plurality of blades has a second natural frequency different from the first natural frequency. A method of fabricating a bladed rotor is also presented.
    Type: Grant
    Filed: April 20, 2015
    Date of Patent: January 14, 2020
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Bruce Fielding
  • Patent number: 10533421
    Abstract: The invention relates to a steam turbine rotor wherein the inter blade region rotor surface, the feed region rotor surface, the piston region rotor surface and the stress relief groove rotor surface of the rotor are configured and arranged as steam exposed surfaces during normal operation of the steam turbine rotor. The steam turbine rotor has a thermal barrier coating on at least the piston region rotor surface.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: January 14, 2020
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Mageshwaran Ramesh, Thomas Schreier, Ingo Kuehn, Gregoire Etienne Witz
  • Patent number: 10533450
    Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: January 14, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Colin J. Kling, Darin S. Lussier, Mark W. Costa
  • Patent number: 10519809
    Abstract: Assemblies and methods useful for mounting an engine to an aircraft structure are disclosed. An exemplary assembly comprises a body made of a magnesium-based material defining a socket formed therein and a liner disposed in the socket for receiving and interfacing with an engine mounting element of the aircraft. The liner comprises a peripheral side wall and a bottom wall having an outer periphery in sealing engagement with a lower portion of the peripheral side wall. The liner is made of a liner material that provides a galvanic potential between the liner material and a material of the engine mounting element that is lower than a galvanic potential between the magnesium-based material of the body and the material of the engine mounting element.
    Type: Grant
    Filed: October 21, 2016
    Date of Patent: December 31, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eric Wintgens, Pierre Samson, Catherine B-Morency, Manon Bolduc
  • Patent number: 10502130
    Abstract: A composite thermal barrier coating (TBC) may be applied to a surface of components within an internal combustion engine. The composite TBC provides low thermal conductivity and low heat capacity insulation that is sealed against combustion gasses. The composite TBC includes three layers, bonded to one another, i.e., a first (bonding) layer, a second (insulating) layer, and a third (sealing) layer. The insulating layer is disposed between the bonding layer and the sealing layer. The bonding layer is bonded to the component and to the insulating layer. The insulating layer includes hollow microspheres that are sintered together to form insulation that provides a low effective thermal conductivity and low effective heat capacity. The sealing layer is a thin film that is configured to resist the high temperatures, present within the engine. The sealing layer is impermeable to gasses and presents a smooth surface.
    Type: Grant
    Filed: February 15, 2017
    Date of Patent: December 10, 2019
    Assignee: GM Global Technology Operations LLC
    Inventors: Russell P. Durrett, Paul M. Najt, Peter P. Andruskiewicz, IV, Jason R. Traub, Michael J. Walker
  • Patent number: 10480530
    Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.
    Type: Grant
    Filed: August 25, 2017
    Date of Patent: November 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Mark W. Costa
  • Patent number: 10472985
    Abstract: A turbine engine has an engine case with an inlet and an interior of the engine. A bearing is disposed on a portion of the engine case. A fan is disposed within the engine and rotates with operation of the engine. The fan includes a plurality of fan blades, and each fan blade is secured at a first end to a disk. A second end of each fan blade is disposed adjacent to the bearing. The portion is oriented relative to the fan such that a reaction force of a fan blade impacting the bearing is directed axially or away from the inlet.
    Type: Grant
    Filed: December 12, 2016
    Date of Patent: November 12, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Milind Khare, Srinivas Chinthapally, Avinash Kumar, Venkatarao Ganji, Theodore Brockett
  • Patent number: 10465715
    Abstract: A blade of a gas turbine engine may comprise a cavity defined, at least partially, by a first interior surface of the blade and by a second interior surface of the blade. A first rib and a second rib may extend from the first interior surface. A third rib may extend from the second interior surface and may be located between the first rib and the second rib. A bulkhead rib may traverse the cavity and may separate the cavity into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: November 5, 2019
    Assignee: GOODRICH CORPORATION
    Inventor: Thomas A. Pollack
  • Patent number: 10465533
    Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Victor John Morgan, Jacob John Kittleson, Andres Jose Garcia-Crespo, Benjamin Paul Lacy
  • Patent number: 10443573
    Abstract: A wind turbine comprising a support structure and one or more turbine blades is disclosed, that incorporates means for reducing the radar cross section (RCS), wherein the support structure is notionally divided into an upper section in the shadow of the blade sweep area, and a lower section beneath the upper section, wherein the upper section is adapted to have the means for reducing the RCS, and the lower section does not have the said adaptation. The invention makes use of the realization that the blade masking the tower as it rotates (or the blade being masked by the tower if facing away from a radar), contributes significantly to interference to radar systems, and so localized application of e.g. RAM can give good RCS reduction at a lower cost than treating the whole structure.
    Type: Grant
    Filed: July 30, 2014
    Date of Patent: October 15, 2019
    Assignee: QINETIQ LIMITED
    Inventors: Greg Peter Wade Fixter, Christopher Douglas James Spooner, Christopher James Perry, Vincent Savage
  • Patent number: 10436220
    Abstract: The invention relates to a method of producing a low-pressure compressor stator for an axial turbine engine. The stator comprises an external shroud with stubs and an annular row of stator blades extending radially towards the inside from the stubs. The method comprises the following stages: supply or production of a starting bar; bending of the bar so that it makes a circle, in order to form an unwrought external shroud; turning to form an axial annular wall delimited by annular fixing flanges; orbital friction-welding of a row of blades onto the stubs of the external shroud. The stubs are realized during a milling stage of the bar or of the external shroud, the milling being carried out before or after the bending stage. The shroud and the blades can be produced in titanium or in a thermoplastic polymer.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: October 8, 2019
    Assignee: Safran Aero Boosters SA
    Inventor: Francois Hindryckx
  • Patent number: 10422074
    Abstract: A carbon fiber material is coated with nanoparticles, where the coating contains from 0.01 to less than 10% by weight of nanoparticles, based on the dry weight of the coated fiber material, and the coating may optionally be involved in further reactions.
    Type: Grant
    Filed: March 7, 2016
    Date of Patent: September 24, 2019
    Assignee: Evonik Degussa GmbH
    Inventors: Stephan Sprenger, Matthias Naumann
  • Patent number: 10415407
    Abstract: An airfoil includes an airfoil section that defines an airfoil profile, and a first endwall section with which the airfoil section is attached. First and second airfoil pieces form different portions of the airfoil profile. The first and second airfoil pieces include respective first ends. The first ends interlock with the first endwall section such that the first and second airfoil pieces are retained with the first endwall section.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Raymond Surace, Tracy A. Propheter-Hinckley
  • Patent number: 10415399
    Abstract: A composite fiber stator ring for a gas turbine engine compressor includes a plurality of composite fiber vane structures. Each of the composite fiber vane structures includes a plurality of fiber plies. All of the fiber plies flow in a single direction at each joint of the corresponding composite fiber vane structure. The plurality of composite fiber vane structures are arranged circumferentially in a ring.
    Type: Grant
    Filed: August 30, 2017
    Date of Patent: September 17, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael G. Ducharme, Farruqh Shahab
  • Patent number: 10392951
    Abstract: A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one spring that mechanically traps the segmented vane structures in radial compression between the inner and outer rings.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: August 27, 2019
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Carr, Bryan P. Dube, Shelton O. Duelm
  • Patent number: 10383282
    Abstract: An airflow system that has a fan spacer within a fan assembly is provided for use with equipment such as work vehicles, which may include agricultural implements or other agricultural equipment. The fan spacer influences a width dimension of a fan housing interior and airflow characteristics of the fan assembly, such as output pressure and flow rate, to optimize fan performance for a particular implementation. In this way, the fan spacer allows for highly customizable fan performances by using housing spacers to modify fan housing dimensions and provide performance characteristics that correspond to what is needed for particular implementations while using common fan housing segments.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: August 20, 2019
    Assignee: CNH Industrial Canada, Ltd.
    Inventors: Ka Po Catherine Hui, Martin J. Roberge, Dennis George Thompson
  • Patent number: 10370988
    Abstract: Described is a nozzle guide vane assembly may comprise: a plurality of nozzle guide vane passages arranged in an annular array, each nozzle guide passage comprising inner and outer radial platforms, a suction surface of a first vane, and a pressure surface of a second vane, wherein the nozzle guide passages are made from a plurality of layers of ceramic fibers held in a ceramic matrix, wherein a first nozzle guide passage includes at least one attachment lug attaching the nozzle guide passage to either or both of an engine casing and an adjacent second nozzle guide passage, the attachment lug being integral with the first nozzle guide passage.
    Type: Grant
    Filed: July 19, 2016
    Date of Patent: August 6, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Steven Hillier
  • Patent number: 10358913
    Abstract: A progressive cavity positive displacement motor having a rotor and stator includes a measurements-while-drilling (“MWD”) tool disposed within the rotor. The motor may use one or more alignment members to measure the position of the rotor relative to the stator. The MWD tool can collect data regarding physical properties such as orientation, temperature, pressure, and other properties. The MWD tool incorporated in the rotor is configured to measure differential properties near or at the uphole and downhole ends of the motor.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: July 23, 2019
    Assignee: SCHLUMBERGER TECHNOLOGY CORPORATION
    Inventor: Edward Richards