With Passage In Blade, Vane, Shaft Or Rotary Distributor Communicating With Working Fluid Patents (Class 415/115)
  • Patent number: 10436049
    Abstract: An airfoil includes an airfoil section with a dual airfoil profile. The airfoil section includes a double wall. The double wall has an outer wall that defines a primary leading end of the dual airfoil profile and an inner wall that defines a secondary leading end of the dual airfoil profile. The inner wall is spaced from the outer wall.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: October 8, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10436038
    Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.
    Type: Grant
    Filed: May 24, 2016
    Date of Patent: October 8, 2019
    Assignee: General Electric Company
    Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
  • Patent number: 10437941
    Abstract: Systems and methods are provided for modeling fluid flow in a turbomachine. A specification of a system is received. The system includes multiple passages, where the multiple passages include at least an inlet guide vane, a rotor, and a stator. A computational grid is generated with a processing system based on the received specification. Governing flow equations for the system are transformed based on inclination parameters, where each passage of the system has an associated inclination parameter. A rotational velocity of rotating passages included in the system is specified, and a time-step for stationary passages included in the system is specified. Time-steps for the rotating passages included in the system are computed, where the time-steps are computed based on pitch-ratios for adjacent passages of the system. A solution for the system is advanced in time by solving the transformed governing flow equations across the computational grid using computer-based numerical calculations.
    Type: Grant
    Filed: August 11, 2015
    Date of Patent: October 8, 2019
    Assignee: Ansys, Inc.
    Inventors: Laith Zori, Paul Galpin, Rubens Campregher, Phillipe Godin, Juan Carlos Morales
  • Patent number: 10436113
    Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: August 3, 2015
    Date of Patent: October 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Dominic J. Mongillo, Steven Bruce Gautschi, Jaime G. Ghigliotty
  • Patent number: 10428664
    Abstract: A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator, which can comprise a virtual impactor, can have an accelerator for accelerating fluid moving through the virtual impactor such that the flow path is divided into a major flow moving into the interior chamber and a minor flow moving into a particle collector defined within the virtual impactor. The accelerator accelerates the fluid such that particles within the fluid are carried by their momentum into the particle collector with the minor flow, removing the particles from the major flow of fluid moving into the interior chamber.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: October 1, 2019
    Assignee: General Electric Company
    Inventors: Hojjat Nasr, Ronald Scott Bunker, Gregory Michael Laskowski, Erich Alois Krammer
  • Patent number: 10428656
    Abstract: The present invention relates to a gas turbine, in particular an aircraft engine gas turbine having a shaft and a bladed turbine rotor joined therewith that has a first rotor segment which has a downstream rotating cascade of the turbine rotor and bounds a first space in the radial direction, this first space communicating with a first gas passage disposed in the shaft, and has a second rotor segment axially adjacent to the first rotor segment, which has at least one second rotating cascade of the turbine rotor and bounds in the radial direction a second space axially adjacent to the first space, this second space communicating with a second gas passage, wherein the first rotor segment has at least one first discharge opening for the discharge of gas from the first space upstream of the furthest downstream rotating cascade.
    Type: Grant
    Filed: July 19, 2016
    Date of Patent: October 1, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Klaus Pirker, Christoph Lauer
  • Patent number: 10428735
    Abstract: A jet engine, which includes a hollow shaft, a center bent tube which is inserted into the shaft, an annular support portion which protrudes from an inner wall surface of the shaft, and an annular spacer ring which is provided on an outer wall surface of the center bent tube and slidably abuts on the support portion, is provided. The spacer ring includes an outer circumferential surface which has a shape along a surface of the support portion in an axial direction of the shaft, an inner circumferential surface which has a shape along the outer wall surface of the center bent tube in the axial direction of the shaft, and a cut portion in which a portion of the spacer ring is cut.
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: October 1, 2019
    Assignee: IHI Corporation
    Inventors: Shinichi Amano, Yuusaku Oikawa
  • Patent number: 10427213
    Abstract: A turbine blade includes pressure and suction surfaces connected to define an interior through which coolant is passable. First and second pedestal arrays, each include pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from and directly opposed to pedestals of the second pedestal array by gaps respectively defined therebetween.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: October 1, 2019
    Assignee: General Electric Company
    Inventors: Tyler Walton Kasperski, Mark Andrew Jones, Jason Adam Neville
  • Patent number: 10427075
    Abstract: A gas turbine engine includes an engine static structure that provides a flow path. A metering hole is provided in the engine static structure. A strainer is arranged over the metering hole. The strainer includes multiple holes that have a total area that is greater than a metering hole area.
    Type: Grant
    Filed: June 20, 2017
    Date of Patent: October 1, 2019
    Assignee: United Technologies Corporation
    Inventors: Timothy J. Jennings, Christopher Whitfield, David Richard Griffin, Christopher Cosher
  • Patent number: 10428663
    Abstract: An airfoil includes an airfoil section that has an internal cavity and first and second endwall sections between which the airfoil section is disposed. The first endwall section includes a guide portion that has a guide opening flanked by first and second bearing lands. The first bearing land is between the guide opening and a first port in the first endwall section that opens to the internal cavity of the airfoil section. The second bearing land is between the guide opening and a second port in the first endwall section that also opens to the internal cavity. A tie member extends through the internal cavity and secures the first and second endwall sections together to trap the airfoil section. The tie member extends through the guide opening in the first endwall section. A spring member on the first and second bearing lands tensions the tie member.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: October 1, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10428659
    Abstract: A flowpath component for a gas turbine engine includes a leading edge, a trailing edge connected to the leading edge via a first surface and a second surface, an impingement cavity internal to the flowpath component, the impingement cavity being aligned with one of the leading edge and the trailing edge, a cooling passage extending at least partially through the flowpath component, and a plurality of crossover holes connecting the cooling passage to the impingement cavity. At least one of the crossover holes is aligned normal to an expected direction of fluid flow through the cooling passage and is unaligned with an axial line drawn perpendicular to a stacking line of the flowpath component.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: October 1, 2019
    Assignee: United Technologies Corporation
    Inventors: Benjamin F. Hagan, Matthew A. Devore, Dominic J. Mongillo, Ryan Alan Waite
  • Patent number: 10422532
    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 section. The combustor includes a combustor region defined by at least one bulkhead panel and at least one heat shielding panel inside the combustor region. The at least one heat shielding panel is connected to the bulkhead panel via at least one cooled fastener.
    Type: Grant
    Filed: July 22, 2014
    Date of Patent: September 24, 2019
    Assignee: United Technologies Corporation
    Inventors: Andreas Sadil, Jonathan M. Jause, Alexander Broulidakis
  • Patent number: 10422230
    Abstract: A gas turbine engine component having a cooling hole includes a first wall having a cooling hole inlet, a second wall generally opposite the first wall and having a cooling hole outlet, a metering section extending downstream from the inlet and having a hydraulic diameter (dh), and a diffusing section extending from the metering section to the outlet. The metering section includes a substantially convex first surface extending from a first end to a second end, a substantially concave second surface extending from a third end to a fourth end, and first and second curved portions connecting the ends of the first and second surfaces.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: September 24, 2019
    Assignee: United Technologies Corporation
    Inventors: Scott D. Lewis, Mark F. Zelesky, Dominic J. Mongillo
  • Patent number: 10415397
    Abstract: Ceramic matrix composite airfoils for gas turbine engines are provided. In an exemplary embodiment, an airfoil includes opposite pressure and suction sides extending radially along a span. The pressure and suction sides define an outer surface of the airfoil. The airfoil further includes opposite leading and trailing edges extending radially along the span, the pressure and suction sides extending axially between the leading and trailing edges. The airfoil also includes a filler pack defining the trailing edge; the filler pack comprises a ceramic matrix composite material. Moreover, the airfoil includes a plenum defined within the airfoil for receiving a flow of cooling fluid, and a cooling passage defined within the filler pack for directing the flow of cooling fluid from the plenum to the outer surface of the airfoil. Methods for forming airfoils for gas turbine engines also are provided.
    Type: Grant
    Filed: May 11, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventor: Kirk Douglas Gallier
  • Patent number: 10415428
    Abstract: A component for a gas turbine engine according to example of the present disclosure includes a body that has an airfoil extending between a radially inner platform and a radially outer platform, and that has an internal cavity within the airfoil. A baffle is disposed within the internal cavity. The baffle defines first and second baffle cavities that are separated by a baffle dividing wall extending between the radially inner platform and the radially outer platform. An impingement plate is spaced apart from one of the radially inner and outer platforms, includes a first opening that provides fluid communication between a first chamber and the first baffle cavity, and includes a plurality of second openings that are smaller than the first opening and provide fluid communication between the first chamber and the second baffle cavity via a second chamber.
    Type: Grant
    Filed: January 31, 2018
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Corey D. Anderson
  • Patent number: 10415408
    Abstract: A component for a gas turbine engine includes a hot side wall, a plurality of connection walls, and a cold side wall. The hot side wall is exposed to a core air flowpath defined by the gas turbine engine. The cold side wall is spaced from the hot side wall and rigidly connected to the hot side wall through the plurality of connection walls. The hot side wall, connection walls, and cold side wall together define a cooling air cavity. The cold side wall defines a thermal stress relief slot for at least partially accommodating a relative thermal expansion between the hot side wall and the cold side wall to reduce an amount of thermal stress within the component during operation of the component.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 10415398
    Abstract: A turbine blade according to the invention includes a first wall surface facing a cooling passage through which cooling air flows; a second wall surface facing a working fluid passage through which a working fluid flows; a communication hole establishing communication between the cooling passage and the working fluid passage; and a projection provided on the downstream side of the flowing direction of the cooling air in the opening of the communication hole formed in the first wall surface, the projection protruding from the first wall surface toward the cooling passage. The projection includes a slope section formed on the first wall surface that ascends in the direction opposite the flowing direction of the cooling air toward the cooling passage and a curved section formed as a convex section on the side of the cooling passage, the curved section extending along the opening in the form of an arc.
    Type: Grant
    Filed: January 30, 2018
    Date of Patent: September 17, 2019
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventor: Ichiro Miyoshi
  • Patent number: 10415416
    Abstract: A fluid flow assembly may include an orifice plate having a set of orifices and a plenum defined by a blade outer air seal. The set of orifices may be aligned with and in fluid communication with the plenum. A gas turbine engine may include a vane outer support having an orifice plate, wherein the orifice plate includes a plurality of sets of orifices. The gas turbine engine may also include a blade outer air seal defining a plurality of plenums. Each set of orifices of the plurality of sets of orifices may be forward relative to and substantially axially aligned with a respective plenum of the plurality of plenums.
    Type: Grant
    Filed: September 9, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, Brian C. McLaughlin
  • Patent number: 10415468
    Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.
    Type: Grant
    Filed: February 6, 2012
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: William K. Ackermann, Peter M. Munsell
  • Patent number: 10408065
    Abstract: A turbine component includes a rail coolant directing chamber radially outward from an airfoil chamber and radially inward from a tip plate. The chamber includes an inlet fluidly coupled to the airfoil chamber to receive a coolant flow therefrom. A plurality of outlets from the rail coolant directing chamber direct the coolant flow to the at least one rail cooling passage in the rail. At least one directing wall is within the rail coolant directing chamber to direct the coolant flow towards one or more of the plurality of outlets located along at least one of the pressure side wall and an aft region of the suction side wall prior to other outlets.
    Type: Grant
    Filed: December 6, 2017
    Date of Patent: September 10, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Nicholas William Rathay, Thomas Earl Dyson, Jay Matthew Lang, Anthony William Mott
  • Patent number: 10408090
    Abstract: An airfoil includes an airfoil structure that has an interior cavity, a preloaded compliant member in the interior cavity, and a panel that defines a portion of an airfoil profile. The preloaded compliant member compliantly retains the panel in a seated position on the airfoil structure.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: September 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10408088
    Abstract: A gas-turbine engine is provided comprising a high-pressure turbine, a low-pressure turbine aft of the high-pressure turbine, and a housing around the low-pressure turbine and the high-pressure turbine. A stator may be disposed between the low-pressure turbine and the high-pressure turbine with a boss formed on the stator. A bushing may be retained in the boss with a pin coupled to the housing and partially within the bushing. A method of mounting a full-ring stator is also provided, the method including the steps of inserting a bushing into a boss of the full-ring stator by press fitting, and inserting a pin into the bushing of the full-ring stator.
    Type: Grant
    Filed: September 14, 2015
    Date of Patent: September 10, 2019
    Assignee: United Technologies Corporation
    Inventors: Steven D. Porter, John T. Ols
  • Patent number: 10408076
    Abstract: The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) is defined by a rim (2a) and comprises at least one inner rib (3) that is spaced apart from the rim (2a) defining the squealer tip (2). The invention is characterized in that said inner rib (3) is shaped to define, inside the squealer tip, a cavity (4) inside of which the passage of leak flows (5) is limited, wherein an upstream opening (131) is made in the rim (2a) at the leading edge (13), and a downstream opening (141) is made in the rim (2a) at the trailing edge (14).
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: September 10, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Remi Philippe Oswald Olive, Cis Guy Monique De Maesschalck, Sergio Lavagnoli, Guillermo Paniagua
  • Patent number: 10400627
    Abstract: In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: September 3, 2019
    Assignee: General Electric Company
    Inventors: Wei Ning, Dennis Paul Dry, Mullahalli Venkataramaniah Srinivas
  • Patent number: 10393381
    Abstract: Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor and turbine portions are integrally formed as a single unitary structure that defines an outer boundary of the flow path. As another example, a flow path assembly comprises a combustor dome positioned a forward end of a combustor; an outer wall extending from the combustor dome through at least a first turbine stage; and an inner wall extending from the combustor dome through at least a combustion section. The combustor dome extends radially from the outer wall to the inner wall and is integrally formed with the outer and inner walls as a single unitary structure.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: August 27, 2019
    Assignee: General Electric Company
    Inventors: Mark Eugene Noe, Shawn Michael Pearson, Joshua Tyler Mook, Brandon ALlanson Reynolds, Jonathan David Baldiga
  • Patent number: 10392944
    Abstract: Various aspects include a turbomachine component, along with a turbomachine and related storage medium. In some cases, the turbomachine component includes: a body defining an inner cavity, the body having an outer surface and an inner surface opposing the outer surface, the inner surface facing the inner cavity; and a mount coupled with the inner surface of the body, the mount including: an impingement baffle coupled with and separated from the inner surface of the body, the impingement baffle including a set of apertures configured to permit flow of a heat transfer fluid therethrough to contact the inner surface of the body; and a reclamation channel connected with the impingement baffle for reclaiming the heat transfer fluid.
    Type: Grant
    Filed: July 12, 2016
    Date of Patent: August 27, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James Albert Tallman, Gary Michael Itzel
  • Patent number: 10393024
    Abstract: A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.
    Type: Grant
    Filed: August 29, 2016
    Date of Patent: August 27, 2019
    Assignee: United Technologies Corporation
    Inventors: Michael S. Stevens, Brian C. McLaughlin
  • Patent number: 10386069
    Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
    Type: Grant
    Filed: June 13, 2013
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: Shawn Michael Pearson, Robert Frederick Bergholz, Douglas Ray Smith, Frederick Alan Buck, Stephen Mark Molter, Kevin Robert Feldmann
  • Patent number: 10386066
    Abstract: A multi-walled structure is provided for a turbine engine. This structure includes a shell with a textured first surface, and a heat shield with a second surface. The heat shield is attached to the shell. The first and the second surfaces vertically define a cooling cavity between the shell and the heat shield. The cooling cavity fluidly couples a plurality of cooling apertures defined in the shell with a plurality of cooling apertures defined in the heat shield.
    Type: Grant
    Filed: November 21, 2014
    Date of Patent: August 20, 2019
    Assignee: United Technologies Corpoation
    Inventors: Frank J. Cunha, Stanislav Kostka, Jr.
  • Patent number: 10385720
    Abstract: A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: John D. Teixeira, Thomas N. Slavens, Raymond Surace
  • Patent number: 10385728
    Abstract: A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Eric A. Grover, John D. Teixeira
  • Patent number: 10378372
    Abstract: A turbine, in particular a high-pressure turbine, for an aircraft engine, with a housing at which turbine guide vanes are circumferentially arranged, wherein the turbine guide vanes have at least one interior space through which cooling air flows during operation of the turbine. At least one turbine guide vane has a cooling air passage in the area of an inner wall with respect to the radial direction of the turbine, via which the interior space of the turbine guide vane can be supplied with cooling air.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: August 13, 2019
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Dimitrie Negulescu, Jens Taege, Joana Negulescu, Knut Lehmann
  • Patent number: 10378363
    Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: August 13, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher Whitfield, Carey Clum, Mark Borja
  • Patent number: 10378364
    Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
    Type: Grant
    Filed: November 7, 2017
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Edwin Otero, David R. Pack
  • Patent number: 10378361
    Abstract: A gas turbine blade according to an embodiment of the present invention includes a turbine blade provided in a gas turbine; and a plurality of film coolers formed in a section from a leading edge to a trailing edge of the turbine blade, in which the film cooler includes a cooling channel through which cooling air is introduced and formed in an oval shape; and an outlet through which the cooling air passing through the cooling channel is discharged and extending from an extended end of the cooling channel toward an outer side thereof and formed in an oval shape.
    Type: Grant
    Filed: August 16, 2017
    Date of Patent: August 13, 2019
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Ki Don Lee, Seok Beom Kim
  • Patent number: 10378380
    Abstract: A system includes a shroud segment for use in a turbine and includes a body having a leading and trailing edge, first and second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges. A first lateral side interfaces with a cavity having a cooling fluid. A first channel includes a first and second end portion. A second channel includes a third end portion and a fourth end portion. The first and second channels receive the cooling fluid from the cavity to cool the body. The second end portion includes a first segmented channel with first metering feature and the third end portion includes a second segmented channel with second exit feature. The first and second exit features meter a flow of the cooling fluid within the first and second channels.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: August 13, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Marc Lionel Benjamin, Benjamin Paul Lacy, Luis Alfonso Gonzalez, Michael Scott Soden
  • Patent number: 10378770
    Abstract: Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The inner wall and the unitary outer wall define a combustor of the combustion section. In another exemplary embodiment, a flow path assembly comprises a unitary inner wall defining an inner boundary of a flow path and extending from a forward end of a combustor through a nozzle portion of a first turbine stage, and a unitary outer wall defining an outer boundary of the flow path and extending from the forward end of the combustor through at least the first turbine stage.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Andrew Scott Bilse, Mark Eugene Noe, Brett Joseph Geiser
  • Patent number: 10371000
    Abstract: A pressure and temperature probe includes a probe head, a probe tip extending from the probe head and ending with a sensor face, a pressure channel extending into the probe tip through the sensor face, and a temperature channel extending into the probe tip through the sensor face. A pressure sensor is in fluid communication with a pressure channel and a temperature sensor in fluid communication with the temperature channel. The temperature channel extends parallel to the pressure channel, and the temperature channel is fluidly separate from the pressure channel. The sensor face can be configured to minimally intrude the flowpath of a working fluid, thereby minimizing disruption of the flowpath. The probe can be configured on a gas turbine engine.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: August 6, 2019
    Assignee: Rosemount Aerospace Inc.
    Inventor: Lisa Graham
  • Patent number: 10371056
    Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.
    Type: Grant
    Filed: December 10, 2015
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu, William K. Ackermann
  • Patent number: 10371166
    Abstract: A seal spacer for a gas turbine engine to provide sealing between a casing wall and a stator vane of the engine. The seal spacer comprises a circumferential body having a slot defined therethrough and configured to receive the stator vane therein. The circumferential body is configured to be disposed between and space apart the engine casing wall from a head of the stator vane when the vane is inserted in the slot and the vane is inserted in the opening in the casing wall. The circumferential body includes a support positioned to be engage and provide a gap between the casing wall and the head when the seal spacer is installed therebetween, and an elastomeric seal portion positioned to engage and compressingly provide sealing the casing wall and the head when the seal spacer is installed therebetween to seal the gap.
    Type: Grant
    Filed: December 16, 2016
    Date of Patent: August 6, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tibor Urac, Bernadette Mason
  • Patent number: 10370986
    Abstract: Nozzles and nozzle assemblies for gas turbine engines are provided. A nozzle includes an airfoil having an exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, an outer band disposed radially outward of the airfoil, the outer band including a radially outwardly-facing end surface, and an inner band disposed radially inward of the airfoil, the inner band including a radially inwardly-facing end surface. The nozzle further includes a flange extending radially from one of the radially outwardly-facing end surface or the radially inwardly-facing end surface. The flange is formed from a ceramic matrix composite material and includes a plurality of ceramic matrix composite plies stacked together and generally having an L-shape in a circumferential cross-sectional view.
    Type: Grant
    Filed: July 24, 2015
    Date of Patent: August 6, 2019
    Assignee: General Electric Company
    Inventors: Bryce Loring Heitman, Gregory Scott Phelps, Darrell Glenn Senile
  • Patent number: 10371154
    Abstract: An apparatus, system and method for pumping gaseous fluid are described. The gas separator of the invention homogenizes at least a portion of produced well fluid and vents unhomogenized gas, improving the efficiency and decreasing the downtime of the assembly. A system for pumping gaseous fluid from an underground well includes a gas separator, the gas separator including an impeller configured to homogenize at least a portion of a gas and a liquid in a pumped fluid to obtain homogenized fluid, the impeller including a top side open to the diffuser and a truncated vane located at a mid-pitch location between at least two untruncated vanes starting from a bottom side of the impeller, and a gas separation chamber downstream of the impeller, the gas separation chamber configured to vent an unhomogenized gas, and a centrifugal pump arranged to receive the homogenized fluid from the gas separation chamber.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: August 6, 2019
    Assignee: Halliburton Energy Services, Inc.
    Inventors: Shiv Jayaram, Freddie George Walton, David Thomas Jolly, Steven Keith Tetzlaff
  • Patent number: 10370300
    Abstract: A turbine system includes a turbine shroud segment. The turbine shroud segment includes a backside, a flow path surface opposite to the back side and configured to be disposed adjacent a hot gas path of the turbine system, and side walls extending between the backside of the turbine shroud segment and the flow path surface of the turbine shroud segment. The turbine shroud segment also includes cooling channels disposed in a thickness of the turbine shroud segment between the backside and the flow path surface, where each cooling channel includes an outlet at one of the side walls of the turbine shroud segment.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: August 6, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Carlos Bonilla Gonzalez, Eric John Ruggiero, Jason Randolph Allen
  • Patent number: 10370982
    Abstract: A turbine blade comprises a leading edge, a trailing edge, a squealer tip floor, and one or more walls arranged to form a cooling circuit within the turbine blade, the one or more walls forming an impingement shelf having one or more impingement holes through which coolant is expelled to cool the turbine blade.
    Type: Grant
    Filed: February 3, 2017
    Date of Patent: August 6, 2019
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Steven Roberts
  • Patent number: 10364681
    Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: July 30, 2019
    Inventors: Matthew Lee Krumanaker, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
  • Patent number: 10364691
    Abstract: A turbomachine subassembly has a radially inner shell and a radially outer shell of an annular gas flow path. A radial arm extends radially between the radially inner and outer shells and delimits an isolated volume which is connected to an inner volume of a chamber partly delimited by the radially inner shell. A segment of a conduit extends radially in the isolated volume, and a ventilation air supply source is connected to supply ventilation air to the isolated volume, whereby ventilation air may be supplied to the chamber through the isolated volume. An external radial end of the radial arm supports a first connection box that closes it off. The internal volume of the radial arm communicates with the ventilation air supply source. An external cylindrical wall of the first connection box fits inside an internal cylindrical wall of the external radial end of the radial arm.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: July 30, 2019
    Assignee: Safran Aircraft Engines
    Inventors: Augustin Marc Michel Curlier, Nicolas Aussedat
  • Patent number: 10364682
    Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: July 30, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew Andrew Hough, Jeffrey S. Beattie
  • Patent number: 10364680
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.
    Type: Grant
    Filed: August 14, 2012
    Date of Patent: July 30, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Bret M. Teller, Mark F. Zelesky, Scott D. Lewis, Brandon W. Spangler, Ricardo Trindade
  • Patent number: 10364683
    Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Brooks E. Snyder, Thomas N. Slavens, Nicholas M. LoRicco, James T. Auxier
  • Patent number: 10358927
    Abstract: A retainer that protrudes from an inner shroud of a vane to a radially inner side and extends in a circumferential direction is formed with an opening that passes through the retainer in an axial direction and defines a space through which air flows. A width of the opening in the circumferential direction is wider than a width of a vane body in the circumferential direction at a radially inner end of the vane body at a position of the retainer in the axial direction.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: July 23, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshifumi Okajima, Masamitsu Kuwabara