Patents Examined by Jason Shanske
  • Trunnion for high-pressure turbine, and turbojet engine including such a trunnion
    Patent number: 10113480
    Abstract: The invention relates to a trunnion (23) for a high-pressure turbine (11), to be arranged between a shaft of a low-pressure turbine (9) and an inner surface (34) of a seal mounting (26) of the low-pressure turbine (8), the trunnion (23) being characterized in that it includes a drop-launching extension (32) arranged such as to extend opposite a flared portion (33) of the inner surface (34) of the seal mounting (26), such that when the trunnion (23) is rotated about the shaft of the low-pressure turbine (9), oil (H2), which tends to penetrate between the trunnion (23) and the seal mounting (26), is thrown by centrifugal effect from the drop-launching extension (32) toward the flared portion (33) of the inner surface (34) of the seal mounting (26).
    Type: Grant
    Filed: June 11, 2014
    Date of Patent: October 30, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Maurice Guy Judet, Laurent Jacques Michel Coulombeau, Fabrice Garin
  • Compound cycle engine
    Patent number: 10107195
    Abstract: A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the first stage turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the second stage turbine of the turbocharger is in fluid communication with the flowpath of the first stage turbine downstream of its rotor. The first stage turbine has a lower reaction ratio than that of the second stage turbine. A method of compounding at least two rotary engines is also discussed.
    Type: Grant
    Filed: June 16, 2015
    Date of Patent: October 23, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Sebastien Bolduc, Mike Fontaine, Luc Landry, Jean Thomassin
  • Turbocharger systems and method to prevent compressor choke
    Patent number: 10107296
    Abstract: Systems and methods are provided for a turbocharger compressor, where the system may comprise: an actuatable annular disk comprising choke slots therein; an outer annular disk comprising choke slots therein; and an actuator to rotate the actuatable annular disk relative to the outer annular disk to vary alignment of the choke slots of the actuatable annular disk and the outer annular disk. The actuator may be controlled by an engine controller responsive to operating conditions of the compressor and actuated to align choke slots. Alignment of the choke slots allows air to be drawn into the impeller effectively expanding the compressor flow capacity to prevent compressor choke.
    Type: Grant
    Filed: June 25, 2013
    Date of Patent: October 23, 2018
    Assignee: Ford Global Technologies, LLC
    Inventors: Harold Huimin Sun, Dave R. Hanna, Thomas Polley, Liangjun Hu, Daniel William Kantrow
  • Gas turbine engine with gearbox health features
    Patent number: 10107135
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.
    Type: Grant
    Filed: October 26, 2015
    Date of Patent: October 23, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Fan assembly
    Patent number: 10100836
    Abstract: A fan assembly includes a nozzle and a device for creating an air flow through the nozzle. The nozzle includes an interior passage, a mouth for receiving the air flow from the interior passage, and a Coanda surface located adjacent the mouth and over which the mouth is arranged to direct the air flow. The mouth and the Coanda surface extend about an axis. The Coanda surface comprises a diffuser portion, the angle subtended between the axis and the diffuser portion of the Coanda surface varying about the axis.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: October 16, 2018
    Assignee: Dyson Technology Limited
    Inventors: Timothy Nicholas Stickney, Christopher Steven Hodgson, James John Bryden
  • Method for heating up a steam turbine or for keeping a steam turbine hot
    Patent number: 10100665
    Abstract: A method for heating up a steam turbine or for keeping a steam turbine hot, which steam turbine has at least one pressure stage working at an initial pressure or intermediate pressure, at least one final pressure stage which is fluidically connected downstream of the pressure stage and works at a final pressure which is lower than the initial pressure or intermediate pressure, and at least one condenser which is connected downstream of the final pressure stage, wherein steam generated outside the steam turbine is introduced into the pressure stage. After flowing through the pressure stage and bypassing the final pressure stage, the steam is supplied directly to the condenser.
    Type: Grant
    Filed: April 29, 2015
    Date of Patent: October 16, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Tobias Hogen, Yevgen Kostenko, Sebastian Zahn, Uwe Zander
  • Oil drain for the bearing housing of a turbocharger
    Patent number: 10100671
    Abstract: An oil drain (8) in a turbocharger bearing housing (1) is provided in which the oil flows out along the outer edge of the oil drain (8) leaving the center of the drain (8) open. Air can flow between the bearing housing (1) and the oil sump allowing for an equalization of air pressure therebetween.
    Type: Grant
    Filed: December 9, 2013
    Date of Patent: October 16, 2018
    Assignee: BorgWarner Inc.
    Inventors: Lauro Takabatake, Douglas Gusmao
  • Methods and systems for producing liquid hydrocarbons
    Patent number: 10099972
    Abstract: Systems and a method are provided for producing an aromatic hydrocarbon and generating electricity from a tail gas stream. The method includes feeding a first stream including a raw natural gas into a reactor. The method includes converting the first stream, at least in part, to a second stream including an aromatic hydrocarbon within the reactor. The method includes separating the second stream into a tail gas stream and a liquid aromatic hydrocarbon stream and combusting at least a portion of the tail gas stream to generate electricity.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: October 16, 2018
    Assignee: ExxonMobil Upstream Research Company
    Inventors: Paul F. Keusenkothen, Timothy A. Barckholtz, J. Tim Cullinane, Robert D. Denton, Frank Hershkowitz, Ian J. Laurenzi
  • Seals for gas turbine engines
    Patent number: 10100660
    Abstract: A turbine shroud for use in a gas turbine engine that includes a metallic carrier, a blade track, and a seal is disclosed. The seal is engaged with surfaces of the metallic carrier and the blade track to block ingress of hot gasses at the interface of the blade track and the metallic carrier.
    Type: Grant
    Filed: January 6, 2016
    Date of Patent: October 16, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Jun Shi, Emil R. DeJulio
  • Impeller for a centrifugal pump
    Patent number: 10094222
    Abstract: The present invention relates to a centrifugal pump, the impeller of which comprises a shroud (34) with at least one solid and rigid working vane (36), and at least one solid and rigid rear vane (38), the at least one working vane (36) having a leading edge region (46), a trailing edge region (48), a central region (C), a side edge, a pressure face (42) and a suction face (44), the at least one solid and rigid rear vane (38) having a trailing edge region, a side edge, a pressure face and a suction face. The trailing edge region (48) of the at least one working vane (36) is rounded by means of a rounding to have a thickness greater than that in the central region (C).
    Type: Grant
    Filed: September 19, 2013
    Date of Patent: October 9, 2018
    Assignee: Sulzer Management AG
    Inventors: Matti Koivikko, Kalle Tiitinen, Sami Virtanen, Jussi Matula
  • Turbocharger lubricant turbine
    Patent number: 10087780
    Abstract: An assembly for a turbocharger can include a shaft and turbine wheel assembly and a component that has a rotational axis and that includes a through bore for receipt of the component by the shaft of the shaft and turbine wheel assembly where the component includes an inner surface and an outer surface and one or more passages that extend between the inner surface and the outer surface, where the one or more passages are shaped to exert force on the component responsive to flow of fluid in the one or more passages and where the force rotates the component about the rotational axis. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: October 2, 2018
    Assignee: Honeywell International Inc.
    Inventors: Poomkuzhimannil Zachariah John, Suryakant Gupta, Parikshit I Mulani, Maltesh Kolur, Giorgio Figura
  • Steam turbine rotor seal key member, related assembly and steam turbine
    Patent number: 10087768
    Abstract: Various embodiments include a rotor key member, along with a related assembly and steam turbine. Particular embodiments include a rotor key member for retaining a circumferential seal in a steam turbine, the rotor key member including: a main body; a first arm extending from the main body; a second arm extending from the main body, wherein the first, arm, the second arm and the main body define a space spanning axially between the first arm and the second arm; and a hook extending from the second arm in a direction axially away from the space, the hook sized to contact a radially inner surface of the circumferential seal.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: October 2, 2018
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, Sean Christopher Morrissey, Nicholas Daniel Viscio
  • Nacelle equipped with an oil-cooling circuit comprising an intermediate heat exchanger
    Patent number: 10087841
    Abstract: The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: October 2, 2018
    Assignee: AIRCELLE
    Inventor: Pierre Caruel
  • Combustor with grommet having projecting lip
    Patent number: 10088162
    Abstract: A combustor includes a shell that bounds at least a portion of a combustion chamber. The shell includes a wall that has an orifice that opens to the combustion chamber. A grommet includes a body portion and a lip that projects from the body portion. The body portion and the lip carry a surface that extends around a passage through the grommet. At least a portion of the lip extends within the orifice of the wall of the shell.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: October 2, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James P. Bangerter, Kevin Joseph Low, Jonathan M. Jause, Robert Sonntag, Reza Rezvani, David Kwoka
  • Seal assembly for a static structure of a gas turbine engine
    Patent number: 10087847
    Abstract: A static structure of a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an outer platform, an inner platform, an airfoil that extends between the outer platform and the inner platform, a service tube disposed at least partially through the airfoil, and a seal assembly that seals between the service tube and one of the outer platform and the inner platform.
    Type: Grant
    Filed: January 31, 2013
    Date of Patent: October 2, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Grace E. Szymanski
  • Heat exchanger arrangement for turbine engine
    Patent number: 10082081
    Abstract: A turbine engine cooling arrangement according to an example of the present disclosure includes, among other things, a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, a second airflow source including a second passage adjacent the first passage for conveying a second airflow, and a heat exchanger that is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow. The first airflow and the second airflow stream over the heat exchanger in a parallel radial direction and a parallel axial direction. An engine inlet divides inlet air into the core flow, the first airflow, and the second airflow. A method of providing cooling air is also disclosed.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: September 25, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael Joseph Murphy, Sean P. Zamora
  • Rotation mechanism and internal unit of rotation mechanism
    Patent number: 10077783
    Abstract: A rotation mechanism includes a casing with an upper half portion and a lower half portion; and an internal unit disposed in the casing with a rotor rotating around an axis thereof. Additionally, a bearing portion rotatably supports the rotor, and an annular seal portion seals a gap surrounding a circumferential surface of the rotor. An axial movement restricting portion includes a fitting concave portion on one of the casing and the internal unit, and a fitting convex portion to be fitted into the fitting concave portion as a pair, which restricts relative movement between the casing and the internal unit in a direction of axis. A tapered surface is formed on the fitting concave portion and the fitting convex portion and a width thereof in the direction of axis increases toward an inner circumferential side in a radial direction.
    Type: Grant
    Filed: September 25, 2012
    Date of Patent: September 18, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Tomohiro Masuda, Atsushi Higashio
  • Tip clearance probe including anti-rotation feature
    Patent number: 10077992
    Abstract: A tip clearance probe includes at least one anti-rotation feature within the probe housing that prevents a sensor component from rotating when the tip clearance probe fails due to extraordinary wear and tear.
    Type: Grant
    Filed: August 31, 2012
    Date of Patent: September 18, 2018
    Assignee: United Technologies Corporation
    Inventor: Eli Cole Warren
  • Composite annular casing of a compressor for a turbo machine
    Patent number: 10077678
    Abstract: The invention relates to a composite annular casing for a low-pressure compressor of a turbo machine, including a wall of generally circular form or in a circular arc; a mounting flange extending radially from one side of the wall, forming an edge together with the wall; a main fibrous reinforcement (38) extending in a continuous manner along the wall and the flange and forming an angled portion and rounded in the area of the edge; an auxiliary fibrous reinforcement (56) extending along the edge; and a matrix. The auxiliary reinforcement (56) comprises a core extending along the edge in such a way as to occupy the volume between the edge and the angled portion of the main reinforcement (38). The invention also relates to a turbo machine comprising a composite annular casing, as well as to a method of manufacturing a composite annular casing of a turbo machine.
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: September 18, 2018
    Assignee: Safran Aero Boosters SA
    Inventor: Benoit Hannecart
  • Gas turbine engine rotor stack assembly
    Patent number: 10077663
    Abstract: A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.
    Type: Grant
    Filed: September 29, 2011
    Date of Patent: September 18, 2018
    Assignee: United Technologies Corporation
    Inventors: Eric W. Malmborg, David P. Houston, James R. Midgley, Robert A. Grelotti, Joseph W. Bridges