Patents Examined by Ninh H. Nguyen
  • Patent number: 11028856
    Abstract: Provided is a centrifugal compressor impeller that includes: a hub; a plurality of full blades that are arranged on the hub in a circumferential direction of rotation; and splitter blades provided between the full blades. There is a line-of-sight direction which is a direction parallel to a virtual plane perpendicular to a rotation axis and in which an entire suction surface of the full blade adjacent to a front side of the splitter blade in a rotational direction, an entire pressure surface of the full blade adjacent to a rear side of the splitter blade in the rotational direction, and an entire surface of the splitter blade are visible.
    Type: Grant
    Filed: April 7, 2017
    Date of Patent: June 8, 2021
    Assignee: IHI Corporation
    Inventors: Takuro Kiriaki, Soumya Dutta
  • Patent number: 11028715
    Abstract: An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.
    Type: Grant
    Filed: October 2, 2018
    Date of Patent: June 8, 2021
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Douglas David Dierksmeier
  • Patent number: 11028824
    Abstract: A wind turbine blade is provided with two shell parts each at least partly made of a sandwich structure including an inner skin (76), an outer skin (74), and an intermediate core material (75, 77), wherein the shell parts are bonded together at least along their respective leading edges (18). The blade also comprises a longitudinally extending spacing section in which the respective trailing edges (58a, 58b) of the pressure side shell part and the suction side shell part are spaced apart, wherein a trailing edge shear web (45) is arranged between and connected to the sandwich structure of the suction side shell part (84, 86, 87) and the sandwich structure of the pressure side shell part (74, 76, 77).
    Type: Grant
    Filed: May 25, 2016
    Date of Patent: June 8, 2021
    Assignee: LM WP PATENT HOLDING A/S
    Inventor: Jesper Hasselbalch Garm
  • Patent number: 11028782
    Abstract: A pressure relief arrangement for a gas turbine engine comprises a hinged door and a mount. A plastically deformable member is provided between and coupled to the hinged door and the mount. The deformable member is configured to deform between a non-deformed state when the door is in a closed position and an elongated deformed state when the door is in an open position.
    Type: Grant
    Filed: September 7, 2018
    Date of Patent: June 8, 2021
    Inventors: Simon M. Ruston, Rong Yang, Matthew Fox, Aniket Anand Kulkarni
  • Patent number: 11028707
    Abstract: The invention concerns a transition duct for a multi-stage compressor of a gas turbine engine. Regions of the inner surface of the duct are provided with a predetermined and dissimilar surface roughness to optimise gas flow efficiency within the duct.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: June 8, 2021
    Assignee: GKN Aerospace Sweden AB
    Inventor: Peter Johansson
  • Patent number: 11028698
    Abstract: A small gas turbine engine with a ceramic turbine to allow for higher turbine inlet temperatures, where a metallic compressor is secured to a ceramic shaft extending from a ceramic turbine to form a single piece ceramic shaft and turbine, where a threaded nut secures a split ring retainer on the compressor end of the ceramic shaft. A hollow thrust runner is compressed between the compressor disk and the turbine disk by the threaded nut to secure rotor together. A centering spring forms a tight fit between the metallic thrust runner and the ceramic shaft on the turbine side.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: June 8, 2021
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Russell B Jones, Edwin L Kite
  • Patent number: 11028709
    Abstract: An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.
    Type: Grant
    Filed: September 18, 2018
    Date of Patent: June 8, 2021
    Assignee: General Electric Company
    Inventors: Vasantharuban Subramanian, Ronald Denmark, Prem Navin Dhayanandam, Richard Gutta, Sanjeev Kumar Jha
  • Patent number: 11022099
    Abstract: A ram air turbine (RAT) can include a housing and a turbine shaft configured to connect to one or more turbine blades and be turned by the one or more blades. The turbine shaft can be disposed in the housing to rotate relative to the housing along a rotational axis. The RAT can include a first bearing and a second bearing mounted between the turbine shaft and the housing to allow the turbine shaft to rotate relative to the housing. The RAT can include a whirl reduction system configured to dampen or eliminate whirl around the rotational axis.
    Type: Grant
    Filed: March 25, 2019
    Date of Patent: June 1, 2021
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Stephen Michael Bortoli, Daniel Kuehn
  • Patent number: 11022134
    Abstract: The present disclosure provides an oil pump including a housing in which a space is formed, a rotor installed to be rotatable in an eccentric position in the housing and having vanes mounted along a circumference direction to be protruded and retracted in a radial direction of the housing, and an inner ring fitted to an inner surface of the housing and rotated along with the rotor when the rotor rotates. The housing is formed of a material harder than the material of the inner ring, and oil for lubrication is provided between the housing and the inner ring.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: June 1, 2021
    Assignees: HYUNDAI MOTOR COMPANY, KIA MOTORS CORPORATION, MYUNG HWA IND. CO., LTD.
    Inventors: Jae-Kyun Doo, Kyung-Hwan Oh, Hyun-Eu Jung
  • Patent number: 11022125
    Abstract: A centrifugal compressor includes: a rotor that includes a shaft rotatably disposed inside a casing and impellers fixed to an outer periphery of the shaft; a diaphragm that surrounds the impellers from an outer peripheral side; a suction-side casing head disposed separately from the diaphragm on a side on which fluid is sucked; a temperature controlling mechanism that is provided inside the suction-side casing head and is configured to control ambient temperature through flow of a heating medium; a heat insulating body disposed between the suction-side casing head and the diaphragm; and a locking structure that locks the heat insulating body and the suction-side casing head with each other to be relatively displaceable in a radial direction.
    Type: Grant
    Filed: February 20, 2018
    Date of Patent: June 1, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Noriyuki Okada, Yuji Masuda
  • Patent number: 11021998
    Abstract: A support assembly for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The support assembly includes an outer race positioned radially exterior to the bearing such that the outer race supports the bearing. Additionally, the support assembly includes a shape memory alloy damper positioned radially exterior to the outer race and at least partially supporting the outer race. Moreover, the shape memory alloy damper includes a plurality of sleeves. One or more sleeves of the plurality of sleeves include a shape memory alloy material.
    Type: Grant
    Filed: August 8, 2019
    Date of Patent: June 1, 2021
    Assignee: General Electric Company
    Inventors: Ravindra Shankar Ganiger, Praveen Sharma, Bhujabal Prashant Mahadeo, Shivam Mittal
  • Patent number: 11021966
    Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: June 1, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Nicholas J. Madonna, Daniel P. Preuss, Kristopher K. Anderson
  • Patent number: 11021962
    Abstract: A turbulent air reducer assembly for a gas turbine engine includes a windage cover attached to a first standoff and a second standoff, the windage cover tuned to a particular vibration response. A method of managing air within a turbine of a gas turbine engine includes reducing turbulence from a multiple of recesses within a tangential on-board injector with a turbulent air reducer assembly within each of the multiple of recesses, the turbulent air reducer assembly tuned to a particular vibration response from a turbine rotor.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Neil L. Tatman, Nathan K. Galle, Richard K. Hayford
  • Patent number: 11022128
    Abstract: An axial fan includes an upper impeller disposed in an axially upper portion of a housing, and an upper circuit board disposed axially below the upper impeller. An upper impeller cup of the upper impeller includes an upper cylindrical portion and an upper lid. The axial fan includes a lower impeller disposed in an axially lower portion of the housing, and a lower circuit board disposed axially above the lower impeller. A lower impeller cup of the lower impeller includes a lower cylindrical portion and a lower lid. An axial upper end outer diameter of the upper cylindrical portion is smaller than an axial lower end outer diameter of the upper cylindrical portion. An axial lower end outer diameter of the lower cylindrical portion is smaller than an axial upper end outer diameter of the lower cylindrical portion.
    Type: Grant
    Filed: May 3, 2019
    Date of Patent: June 1, 2021
    Assignee: NIDEC CORPORATION
    Inventors: Kazuhiro Inouchi, Junya Matsuyama
  • Patent number: 11021986
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends circumferentially between first and second mate faces and an engagement portion along the first mate face. A support has an interface portion that extends from a mounting portion. The interface portion abuts the engagement portion to limit relative movement, and the mounting portion defines an aperture that receives a fastener to mechanically attach the mounting portion to an engine static structure. A portion of the fastener is circumferentially aligned with the first mate face. The fastener defines a first cooling passage that delivers cooling flow at a location adjacent to the first mate face.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: June 1, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Winston Gregory Smiddy, Paul M. Lutjen
  • Patent number: 11015483
    Abstract: Various embodiments include a compressor casing and a method of assembly. The compressor casing comprises a first and an adjacent, second annular casing segments each comprising an annular radially-extending flange with mounting holes; at least one annular recess disposed on at least one annular side mating face of the adjacent flanges of the adjacent segments; at least one set of stress-relief holes disposed through at least one flange of the adjacent segments; and at least one annular leak-resistant plate disposed within the at least one annular recess having at least a third set of mounting holes. All sets of mounting holes are substantially aligned with each other and receive a plurality of respective fasteners, and the at least one annular plate is clamped between the adjacent segments and seals the at least one set of stress-relief holes for preventing leakage therethrough.
    Type: Grant
    Filed: March 9, 2018
    Date of Patent: May 25, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Vishnu Das K, Carlos Ivan Flores, Atanu Saha, Vinaykumar Shrimantrao Patil
  • Patent number: 11015659
    Abstract: A bowed-rotor prevention system for a turbomachine is disclosed. The system comprises a first turbomachine having a first shaft rotatably supported by a plurality of bearings, a second turbomachine having a second shaft rotatably coupled to the first rotatable shaft, and a pump having a third shaft rotatably coupled to the second shaft. The system further includes a gear box having a fourth shaft rotatably coupled to the third shaft by an clutch configured to operate in a freewheel condition when the first shaft is rotating faster than a first predetermined speed, and further configured to rotatably engage the fourth shaft to the third shaft when the first shaft is rotating slower than a second predetermined speed to thereby drive a rotation of the third shaft, wherein the first predetermined speed is faster than the second predetermined speed.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: May 25, 2021
    Assignee: General Electric Company
    Inventors: Vineet Sethi, Randall Kleen
  • Patent number: 11015462
    Abstract: A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.
    Type: Grant
    Filed: May 21, 2019
    Date of Patent: May 25, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Alain De Gaillard, Clément Pierre Postec, Charles-Henri Claude Jacky Sullet
  • Patent number: 11015611
    Abstract: A centrifugal impeller includes a base plate, a wheel cover, and a plurality of twisted blades disposed between the base plate and the wheel cover. Every two adjacent twisted blades form an air duct; and each air duct includes an air outlet along an outer edge of the base plate. Each of the plurality of twisted blades includes a leading edge, a trailing edge, an upper edge, and a lower edge. The upper edge and the lower edge are disposed between the leading edge and the trailing edge, and are opposite to each other. Defining an axis of the device as L1, and a plane passing through the axis L1 of the device as a meridional plane, when the twisted blades rotate around the axis L1, the leading edge intersects with the meridional plane to produce a plurality of intersection points on the meridional plane which form a first curve.
    Type: Grant
    Filed: November 18, 2019
    Date of Patent: May 25, 2021
    Assignee: ZHONGSHAN YIBISI TECHNOLOGY CO., LTD.
    Inventor: Haiming Xu
  • Patent number: 11009029
    Abstract: A reflection mechanism is disposed above a rotor blade. A chamfered surface of the rotor blade is formed to gradually open wide by 0 to 10 degrees toward the downstream side in the rotational direction, from an imaginary line passing through a rotational direction-side tip end point of a horizontal surface and drawn parallel to a rotating shaft. In the reflection mechanism, inclined plates, inclined at a predetermined angle, are arranged radially in the radial direction from a central disc portion. A particle reflected on the chamfered surface of the rotor blade collides with each inclined plate of the reflection mechanism and is then re-reflected and falls in the downstream direction. Since the particle can securely be reflected toward the reflection mechanism, the particle can be prevented from exiting through an inlet port to flow back toward a chamber.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: May 18, 2021
    Assignee: Edwards Japan Limited
    Inventor: Takashi Kabasawa