With Diversely Oriented Inlet Or Additional Inlet For Diverse Fluid (e.g., Heating, Cooling Or Mixed Working Fluid, Etc.) Patents (Class 415/116)
  • Patent number: 10808561
    Abstract: The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.
    Type: Grant
    Filed: May 27, 2018
    Date of Patent: October 20, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Klaus Pirker, Lukasz Sosnowka, Bernd Kislinger, Rudolf Stanka, Marcin Regulski
  • Patent number: 10801354
    Abstract: A gas turbine engine includes a first case, a second case, and a fastener. The first case has a first flange defining a first opening. The second case has a second flange defining a second opening. The second flange abuts the first flange. The fastener extends through the first opening and the second opening. The fastener defines a first bore that extends through a fastener head along an axis towards an outlet port defined by a fastener shank.
    Type: Grant
    Filed: April 25, 2016
    Date of Patent: October 13, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Philip Robert Rioux, Nicholas R. Leslie
  • Patent number: 10801351
    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 from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: October 13, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Kevin L. Rugg, Winston Gregory Smiddy
  • Patent number: 10774742
    Abstract: A compressor rotor includes a first disk and a conical section connected to the first disk. The conical section includes at least one flow hole. A bore cavity is defined between the conical section and the first disk. The bore cavity is arranged in fluid communication with the at least one flow hole. An anti-vortex tube is disposed within the at least one flow hole of the conical section and includes at least one feature arranged in contact with a surface of the conical section to restrict movement of the anti-vortex tube out of engagement with the conical section.
    Type: Grant
    Filed: March 21, 2018
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Konstantinos Panagiotis Giannakopoulos, Erica J. Harvie
  • Patent number: 10774664
    Abstract: A gas turbine having an annular flowpath defined between concentric inner radial and outer radial boundaries. A plenum is positioned just outboard of the outer radial boundary that wraps circumferentially in spaced relation thereto. The height of the plenum is defined radially between a floor and ceiling. The plenum includes an inlet formed through the ceiling at a first end and spaced outlet ports formed through the floor. The plenum includes a divider baffle that spans the width of the plenum and extends between the first end and the second end of the plenum so to divide the plenum into radially stacked first and second compartments. The first compartment connects directly to the inlet, while the second compartment connects directly to the outlet ports. The height of the first compartment tapers between a greater height at the first end and a lesser height at the second end of the plenum.
    Type: Grant
    Filed: June 8, 2017
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: John Rogers Mason, III, Zhongman Ding, John Lesley DuBose
  • Patent number: 10767863
    Abstract: An annular assembly for a gas turbine engine and a method of making the annular assembly. The annular assembly comprises a supporting member comprising metal and including a support hole therethrough, and a liner tile made of ceramic matrix composite material. A plurality of the liner tile form an annular liner to shield hot combustion gases produced by the gas turbine engine. The liner tile is disposed adjacent the supporting member. A connecting member comprising ceramic material has a base element and a stem. The base element is embedded in the liner tile during construction of the liner tile to form an integrated structure therewith. A distal end of the stem passes through the support hole and is mated with a retaining member to retain the liner tile adjacent the supporting member.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: September 8, 2020
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted Joseph Freeman, Bruce E. Varney, Andrew Joseph Lazur
  • Patent number: 10753220
    Abstract: A blade outer air seal includes a base portion that extends between a leading edge and a trailing edge. A forward wall and an aft wall extend radially outward from the base portion to a radially outer portion. The radially outer portion is spaced from the base portion.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: August 25, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, Daniel J. Whitney
  • Patent number: 10738642
    Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The supported component includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend into the carrier to couple the supported component with the carrier.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 11, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Jun Shi, Jeffrey A. Walston, Aaron D. Sippel
  • Patent number: 10731498
    Abstract: The present disclosure relates generally to blade outer air seal section mount including a resilient spring element that acts to provide re-centering forces to the blade outer air seal section when non-uniform forces applied to the blade outer air seal section causing it to move away from its nominal position.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10731562
    Abstract: A combustor panel may comprise a panel wall comprising a proximal surface and a distal surface. A standoff may be formed over the distal surface of the panel wall. An aperture may be formed through the standoff and may extend from a face of the standoff to the proximal surface of the panel wall. The face of the first standoff may be oriented at an angle between 90 degrees and 160 degrees relative to a plane parallel to the distal surface of the panel wall.
    Type: Grant
    Filed: July 17, 2017
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, Jonathan Lemoine
  • Patent number: 10731502
    Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: August 4, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: William K. Ackermann, Matthew P. Forcier, Paul J. Hiester
  • Patent number: 10731472
    Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: August 4, 2020
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10731507
    Abstract: A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: August 4, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Eric W. Engebretsen, Daniel E. Molnar, Jr., Matthew J. Kappes
  • Patent number: 10723196
    Abstract: An HVAC system according to an example of the present disclosure includes a blower rotatable about an axis. The blower has a first blower section and a second blower section fluidly isolated from the first blower section. An inlet assembly at an axial end of the blower includes a first compartment configured to control fluid flow through the first blower section and a second compartment configured to control fluid flow through the second blower section.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: July 28, 2020
    Assignee: AIR INTERNATIONAL (US) INC.
    Inventors: Wayne Wright, Richard Hoyle
  • Patent number: 10718267
    Abstract: Various embodiments of the present disclosure address problems associated with non-uniform flow of cooling air by providing a turbine engine including a cooling air chamber in fluid communication with a cooling air source, a turbine chamber, and multiple conduits fluidly connecting the cooling air chamber and the turbine chamber. The system is configured such that, when cooling air is flowing from a cooling air source the static pressure within the cooling fluid chamber is substantially uniform and such that the mass flow rates of cooling air through the conduits and into the turbine chamber are substantially uniform.
    Type: Grant
    Filed: December 14, 2017
    Date of Patent: July 21, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Matthew M. Miller, Renée M. Wiley
  • Patent number: 10711629
    Abstract: The present disclosure is directed to a method of operating an active clearance control system for an interdigitated turbine engine. The method includes flowing air from a compressor section to a rotatable outer shroud of an interdigitated turbine section; and adjusting the flow of air to the outer shroud based at least on an engine condition of the turbine engine. The present disclosure is further directed to a gas turbine engine including a low speed turbine rotor comprising an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The engine further includes a turbine frame at least partially surrounding the low speed turbine rotor; a seal assembly disposed between the outer shroud of the low speed turbine rotor and the turbine frame; and a fifth manifold coupled to the turbine frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: July 14, 2020
    Assignee: Generl Electric Company
    Inventors: Gert Johannes van der Merwe, Darek Tomasz Zatorski
  • Patent number: 10711796
    Abstract: A multistage centrifugal compressor is described. The compressor comprises a casing and a shaft rotatingly supported in the casing by at least a first bearing and a second bearing. At least one in-between-bearing impeller is mounted on the shaft, between the first bearing and the second bearing. An overhung impeller is mounted at one end of the shaft. A first diaphragm arrangement is further located in the casing. The first diaphragm arrangement comprises return a channel assembly with a plurality of stationary return channel blades defining a plurality of return vanes for redirecting compressed gas from an exit location of the overhung impeller to an inlet location of the in-between-bearings impeller. The first diaphragm arrangement houses one of the first bearing and second bearing.
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: July 14, 2020
    Assignee: NUOVO PIGNONE SRL
    Inventors: Vittorio Michelassi, Ismail Hakki Sezal, Christian Aalburg
  • Patent number: 10697313
    Abstract: A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have a higher temperature capability than that of the wall.
    Type: Grant
    Filed: February 1, 2017
    Date of Patent: June 30, 2020
    Assignee: General Electric Company
    Inventor: Victor Hugo Silva Correia
  • Patent number: 10690055
    Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.
    Type: Grant
    Filed: May 27, 2015
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Curtis Walton Stover, Jonathan Michael Rausch, Satoshi Atsuchi, Gulcharan Singh Brainch, Robert David Briggs, Ronald Scott Bunker, Ambarish Jayant Kulkarni, Michael Alan Meade, Byron Andrew Pritchard, Robert Proctor
  • Patent number: 10689998
    Abstract: Shrouds and methods for forming turbine components are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a cooling passage defined in the shroud, the cooling passage extending generally circumferentially through the shroud.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: David Scott Stapleton, Robert Charles Groves, II
  • Patent number: 10689997
    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 seal body having a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The seal body defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines a plurality of apertures to the internal cavity. A housing is mounted to the seal such that the impingement face is exposed to define a plenum between the housing and the impingement face. The housing defines a plurality of cooling passages, and each of the plurality of cooling passages define a passage axis that is oriented such that a projection of the passage axis intersects the seal body. A method of sealing is also disclosed.
    Type: Grant
    Filed: April 17, 2018
    Date of Patent: June 23, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Winston Gregory Smiddy, Paul M. Lutjen
  • Patent number: 10689982
    Abstract: An impeller for an exhaust gas turbocharger may include a hub main body and blades arranged thereon. The hub main body may be configured as a polygon with a number of segments that may be tilted with respect to one another, the number of the segments corresponding to a number of the blades. Alternatively, the hub main body may have a main surface that faces the blades and undulates in a circumferential direction, a number of the undulations corresponding to the number of the blades.
    Type: Grant
    Filed: August 3, 2016
    Date of Patent: June 23, 2020
    Assignee: BMTS TECHNOLOGY GMBH & CO. KG
    Inventors: Senol Soeguet, Felix Scheerer, Martin Kuhn
  • Patent number: 10669872
    Abstract: The invention relates to an intermediate case for a twin spool turbomachine for an aircraft, comprising at least one lubricant passage and piece (88a) associated with at least one of its vanes (24), comprising a lubricant passage (98a) extending along a passage axis (134a) and opening up into the lubricant duct (55a). The passage axis (134a) and the orifice axis (140a) are also at a spacing from each other along a circumferential direction (91), and a connection piece (125a) through which a connection conduit (142a) passes is firstly partially housed in the vane root (34) so as to create a communication between the connection duct (142a) and the lubricant passage orifice (124a), and secondly is partially housed in an end-piece support device (108a) or in the lubricant passage end-piece (88a), such that the connection conduit (142a) communicates with the lubricant passage (98a) in the end-piece.
    Type: Grant
    Filed: March 27, 2018
    Date of Patent: June 2, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Cédric Zaccardi, Laurent Jablonski, Christophe Paul Jacquemard, Christophe Marcel Lucien Perdrigeon
  • Patent number: 10662779
    Abstract: A gas turbine engine component includes a passage and a wall adjacent the passage. The wall includes a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells. The wall also includes an array of channels. Each of the channels is located proximate a corresponding one of the cells. A coating is disposed over the cells. When the coating degrades the channels open to permit impingement air flow through the channel onto sidewalls of the cells.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: May 26, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Eric A. Hudson, Tracy A. Propheter-Hinckley
  • Patent number: 10662798
    Abstract: Dry gas sealing system for a turbomachine, in particular a turbocompressor, having at least one dry gas seal for sealing a part located on the rotor side of the turbomachine from a part located on the stator side of the turbomachine, and a purifying device for purifying process gas that is extracted from the turbomachine and can be fed to the or each dry gas seal as purified sealing gas following the purification process; the purifying device is designed as a centrifugal device that is integrated into the part located on the rotor side of the turbomachine.
    Type: Grant
    Filed: October 20, 2016
    Date of Patent: May 26, 2020
    Assignee: MAN Energy Solutions SE
    Inventors: Roger Suter, Michael Betschart
  • Patent number: 10662809
    Abstract: A vane cooling system for a gas turbine engine comprises a vane (21) arranged on a stator and having a chamber (23) extending continuously from a radially inner end to a radially outer end of the vane. The vane (21) has; a radially inner inlet (24) and a radially outer inlet (25), a first cooling fluid feed (39) in communication with the radially inner inlet (24) and a second cooling fluid feed (28) in communication with the radially outer inlet (25), The first cooling fluid feed (39) has a higher pressure than the second cooling feed (28). A flow adjustment device (30) is arranged for adjusting a flow of the second cooling fluid feed into the radially outer inlet (25).
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: May 26, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Simon Pitt
  • Patent number: 10655434
    Abstract: A system and method is provided for converting wellhead pressure of natural gas wells, or for converting water head pressure of water towers, to rotational power for operating rotated equipment, such as electrical generators, electrical alternators, pumps, air compressors, and other rotated equipment.
    Type: Grant
    Filed: April 12, 2017
    Date of Patent: May 19, 2020
    Assignee: Airtek Systems Inc.
    Inventor: Darryl Weflen
  • Patent number: 10655475
    Abstract: A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: May 19, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventors: Alan R Maguire, Timothy J Scanlon
  • Patent number: 10648344
    Abstract: A vane cooling system for a gas turbine engine comprises a vane (20a) arranged on a stator and having a chamber (27,28) extending continuously from a radially inner end to a radially outer end of the vane. The vane (20a) has a first inlet (41) and a second inlet (42). A first cooling fluid feed (54) in communication with the first inlet (41) and a second cooling fluid feed (43) in communication with the second inlet (42). The first cooling fluid feed (54) has a higher pressure than the second cooling fluid feed (43). A flow adjustment device (45) is arranged for adjusting a flow of the second cooling fluid feed (43) into the second inlet (42). The chamber is divided by a restrictor plate (25, 26) to provide an inner chamber (27) and a wall-side chamber (28) bordering the inner chamber (27). The first inlet (41) enters the wall-side chamber (28) and the second inlet (42) enters the central chamber (27).
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: May 12, 2020
    Assignee: Rolls-Royce PLC
    Inventor: Simon Pitt
  • Patent number: 10648362
    Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: May 12, 2020
    Assignee: General Electric Company
    Inventors: Robert Charles Groves, II, David Scott Stapleton
  • Patent number: 10648342
    Abstract: An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes at least one cooling hole including a diffusing section and fluidly coupling an exterior of the engine component to an exterior of the engine component.
    Type: Grant
    Filed: December 18, 2017
    Date of Patent: May 12, 2020
    Assignee: General Electric Company
    Inventors: Zachary Daniel Webster, Aaron Ezekiel Smith, Steven Robert Brassfield
  • Patent number: 10648407
    Abstract: A turbine section for a gas turbine engine includes a turbine blade that extends radially outwardly to a radially outer tip and for rotation about an axis of rotation. A blade outer air seal is mounted in a support structure and is arranged radially outward of the outer tip. A flow guide is arranged between the support structure and the blade outer air seal and defines a passage between the flow guide and the blade outer air seal. The passage is configured to communicate air in a generally axial direction.
    Type: Grant
    Filed: September 5, 2018
    Date of Patent: May 12, 2020
    Assignee: United Technologies Corporation
    Inventors: Ken F. Blaney, Thomas E. Clark
  • Patent number: 10641120
    Abstract: A seal segment for a gas turbine engine has a radially outer wall with a first length, a radially inner wall with a second length, and a rib member which extends radially between the outer wall and the inner wall and along the first and second lengths.
    Type: Grant
    Filed: July 25, 2016
    Date of Patent: May 5, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: David John Thomas, Ted Joseph Freeman, Joseph Pan Lamusga
  • Patent number: 10612469
    Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.
    Type: Grant
    Filed: August 1, 2014
    Date of Patent: April 7, 2020
    Assignee: United Technologies Corporation
    Inventors: Vito Guardi, Christopher B. Lyons, Nathan Snape
  • Patent number: 10612408
    Abstract: A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.
    Type: Grant
    Filed: May 6, 2015
    Date of Patent: April 7, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Mark Borja
  • Patent number: 10612465
    Abstract: A particle separator for a turbomachine includes a first portion including a first end and a second end opposite the first end. The turbomachine includes a first wall and a second wall defining a primary fluid passage. The first wall further defines an auxiliary fluid passage. The first end is coupled to the first wall. The second end extends from the first wall into the at least one primary fluid passage and extends in a direction defined by the fluid flow through the primary fluid passage. The second end and the first wall define a fluid diversion passage coupled in flow communication with the primary fluid passage and the auxiliary fluid passage. The fluid diversion passage is configured to divert fluid from the primary fluid passage to the auxiliary fluid passage in a direction at least partially opposed to the fluid flow through the primary fluid passage.
    Type: Grant
    Filed: November 13, 2015
    Date of Patent: April 7, 2020
    Assignee: General Electric Company
    Inventors: Satoshi Atsuchi, Erich Alois Krammer, Corey Bourassa, Byron Andrew Pritchard, Mehmet Dede
  • Patent number: 10605114
    Abstract: A valve device includes a main steam valve that is provided on a steam flow channel, a regulating valve that is provided on the steam flow channel to be connected to the main steam valve in series and that includes a first valve seat and a first valve body, an overload valve that is provided on a branch flow channel which connects a portion of the steam flow channel between the main steam valve and the regulating valve and a steam turbine to each other and that includes a second valve seat and a second valve body, and a driving unit that drives the first valve body and the second valve body as a common driving source of the first valve body and the second valve body such that the first valve body and the second valve body are interlocked with each other.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: March 31, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Tomoaki Nogami, Takuro Koda, Kenichi Nishiyama
  • Patent number: 10605097
    Abstract: A turbine rotor blade comprises: a blade effective part; a snubber disposed on radially outer side of the blade effective part; a platform disposed on radially inner side of the blade effective part; and an implanted part disposed on radially inner side of the platform. A first flow path is formed inside the implanted part for a cooling medium to pass through. A second flow path is formed inside the platform for the cooling medium having passed through the first flow to pass through. A blade effective part flow path is formed inside the blade effective part for the cooling medium having passed through the second flow path to pass through. A snubber flow path is formed inside the snubber for the cooling medium having passed through the blade effective part flow paths to pass through.
    Type: Grant
    Filed: July 12, 2017
    Date of Patent: March 31, 2020
    Assignee: Toshiba Energy Systems & Solutions Corporation
    Inventors: Kazutaka Tsuruta, Shoko Ito, Iwataro Sato
  • Patent number: 10590952
    Abstract: The present disclosure relates generally to a fan nacelle assembly circumferentially surrounding a fan section, the fan nacelle assembly including an inner wall including an inner wall axial length, and an outer wall an outer wall axial length, wherein the outer wall axial length is greater than the inner wall axial length.
    Type: Grant
    Filed: July 21, 2015
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Frederick M. Schwarz
  • Patent number: 10590785
    Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.
    Type: Grant
    Filed: August 11, 2015
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Brandon W. Spangler
  • Patent number: 10577960
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • Patent number: 10577964
    Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
    Type: Grant
    Filed: March 31, 2017
    Date of Patent: March 3, 2020
    Assignee: United Technologies Corporation
    Inventors: Jonathan Ortiz, Raymond Surace, Renee J. Jurek, Tracy A. Propheter-Hinckley
  • Patent number: 10577970
    Abstract: A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a source of cooling air and a turbine shroud configured to extend around blades of a turbine stage and resist gasses from passing the blades without interaction with the blades. The turbine shroud includes a carrier segment comprising metallic materials and a blade track segment comprising ceramic matrix composite materials.
    Type: Grant
    Filed: September 13, 2016
    Date of Patent: March 3, 2020
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Aaron P. Jennings
  • Patent number: 10563531
    Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal including a sealing portion and an engagement portion. A support includes an interface portion and a mounting portion. The interface portion defines a retention slot spaced apart from opposing mate faces. The mounting portion is configured to be fixedly attached to an engine static structure. The engagement portion is dimensioned to be slideably received within the retention slot.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: February 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10557412
    Abstract: An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.
    Type: Grant
    Filed: May 30, 2017
    Date of Patent: February 11, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul W. Baumann, Brian Barainca, Rolf Thorsen, Mark E. Simonds, Gary F. Fowler, Hector M. Pinero
  • Patent number: 10550726
    Abstract: The present disclosure is directed to a gas turbine engine defining an axial centerline, a longitudinal direction, a radial direction, and a circumferential direction. The gas turbine engine includes one or more frames in which the frame defines an inner ring and an outer ring generally concentric to the inner ring about the axial centerline. The frame defines a plurality of struts extended outward along the radial direction from the inner ring to the outer ring. One or more struts define one or more service passages extended at least partially along the radial direction within the strut, and wherein the inner ring, the outer ring, and the struts together define an integral structure.
    Type: Grant
    Filed: January 30, 2017
    Date of Patent: February 4, 2020
    Assignee: General Electric Company
    Inventors: Thomas Ory Moniz, Jordan Tesorero, Joshua Tyler Mook, Jeffrey Donald Clements
  • Patent number: 10551065
    Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, a fan drive gear system, and a turbine section coupled to drive the fan through the gear system. The combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber. There is a bulkhead in the annular combustion chamber, and an annular heat shield is mounted on the bulkhead. The annular heat shield includes a segment that has a forward face and an aft face, a circumferential outer side and a circumferential inner side, a central orifice between the forward face and the aft face, a lip projecting from the forward face around the central orifice, a rail projecting from the forward face, and a plurality of through-holes between the rail and the lip. The rail contacts the bulkhead to define a cavity bounded by the rail, the lip, and the bulkhead.
    Type: Grant
    Filed: May 26, 2016
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Joey Wong, Robert M. Sonntag, Albert K. Cheung, Timothy S. Snyder
  • Patent number: 10544800
    Abstract: Provided are an inlet guide vane and a centrifugal compressor such that air can be caused to efficiently flow in with use of a simple shape. The inlet guide vane is disposed upstream of an impeller in a flow path of a centrifugal compressor. The inlet guide vane has: a plate-shaped plate section that is disposed in the flow path; and a rotation part that causes the plate section to rotate along an axis of rotation aligned with the radial direction of a rotary shaft of the centrifugal compressor. In a cross-section orthogonal to the axis of rotation of the rotation part, the plate section has, at the leading edge thereof on the upstream side of the flow path, a bent part that is tilted with respect to the other portions.
    Type: Grant
    Filed: October 21, 2015
    Date of Patent: January 28, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES THERMAL SYSTEMS, LTD.
    Inventors: Jun Koga, Yasushi Hasegawa, Shintaro Omura
  • Patent number: 10544799
    Abstract: Provided are a centrifugal compressor gas-supplementing structure and a compressor using the foregoing gas-supplementing structure. The centrifugal compressor gas-supplementing structure includes a annular gas-supplementing passage (6) for introducing supplemented gas into a gas passage (5) of a compressor, and an airflow-guiding assembly is provided in the annular gas-supplementing passage (6). The gas-guiding assembly is used for adjusting a direction of the supplemented gas flowing into the gas passage (5), so that an angle between a direction of the supplemented gas flowing into the gas passage (5) and a direction of an airflow in the gas passage (5) falls within a preset range, and a turbulence loss generated when the two passages of gas merge is avoided to the greatest extent, thereby improving cycle efficiency.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: January 28, 2020
    Assignee: GREE ELECTRIC APPLIANCES, INC. OF ZHUHAI
    Inventors: Nan Jiang, Zhiping Zhang, Ruixing Zhong, Caiyun Jiang, Rong Xie, Jianfei Liu, Yuhui Chen, Baoqian Huang, Jing Zhang, Yi Zhou
  • Patent number: 10544701
    Abstract: A turbine shroud assembly is disclosed including an inner shroud, an outer shroud, a shroud dampening pin, and a biasing apparatus. The inner shroud is adjacent to a hot gas path. The outer shroud is adjacent to the inner shroud and distal from the hot gas path, and includes a channel extending from an aperture adjacent to the inner shroud. The shroud dampening pin is within the channel and contacts the inner shroud, and includes a shaft, a contact surface, and a cap. The shaft is within the channel. The contact surface extends through the aperture in contact with the inner shroud. The cap is distal across the shaft from the contact surface. The biasing apparatus contacts the cap, is driven by a pressurized fluid, and provides a biasing force away from the outer shroud along the shroud dampening pin to the inner shroud through the contact surface.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: January 28, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Glenn Curtis Taxacher, John McConnell Delvaux, Matthew Troy Hafner