With Cooling Passage Patents (Class 29/889.721)
  • Patent number: 10704397
    Abstract: The present disclosure provides a core structure comprising a trailing edge section including a plurality of rib-forming apertures (126) defined by a plurality of radially-extending channel elements (130) and axially-extending passage elements (128) and a radially outer low flow framing channel element (134) located adjacent to a radially outer edge (124). The core structure may be used for casting a gas turbine engine airfoil (11). The radially outer framing channel element (134) comprises a plurality of notches (14) extending radially inwardly from the radially outer edge (124). A distal portion (144a) of the notches (140) overlaps in an axial direction with the rib-forming apertures (126) of a first axially-aligned outer row (138a). A radial height of at least one of a first and a second axially-extending passage element (148a, 148b, 150) is greater than a prevalent radial height of other axially-extending passage elements (128) in the core structure.
    Type: Grant
    Filed: April 3, 2015
    Date of Patent: July 7, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Jan H. Marsh, Wayne J. McDonald, Matthew J. Golsen
  • Patent number: 10584593
    Abstract: Airfoils bodies having a first end, a second end, a leading edge, and a trailing edge with a leading edge channel having a first channel wall and a second channel wall that join at a channel base to define the leading edge channel. The leading edge channel extends in a radial direction along the leading edge. A first leading edge impingement cavity is located proximate the leading edge and the first channel wall defines a portion of the first leading edge impingement cavity and a second leading edge impingement cavity with the second channel wall forming a portion of the second leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled such that air flowing from the first leading edge impingement cavity and through the first leading edge impingement hole impinges upon a portion of the second channel wall.
    Type: Grant
    Filed: October 24, 2017
    Date of Patent: March 10, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Carey Clum, Timothy J. Jennings
  • Patent number: 10563523
    Abstract: A method for making a turbine engine blade includes three-dimensionally weaving elongate fibers of a material selected from the group consisting of carbon, glass, silica, silicon carbide, silicon nitride, aluminum, aramid, aromatic polyamide, and combinations thereof to create a woven preform including a single piece of woven material. The woven preform includes continuous warp fibers extending along a first direction, continuous weft fibers extending along a second direction substantially normal to the first direction, and continuous fibers extending in a third direction substantially normal to the first and the second directions. The woven preform includes an airfoil region extending along the first direction and an arrangement of flaps extending along the second direction. The flaps are folded into a plane substantially normal to a plane of the airfoil region to form a shaped woven preform. The shaped woven preform is densified with a ceramic matrix.
    Type: Grant
    Filed: March 29, 2016
    Date of Patent: February 18, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Tara Grant Schetzel
  • Patent number: 10519780
    Abstract: Techniques for forming a dual-walled component for a gas turbine engine that include chemically etching at least one of a hot section part or a cold section part to form an etched part having plurality of support structures and bonding the etched part to a corresponding cold section part or a corresponding hot section part to form a dual-walled component, with the plurality of support structures defining at least one cooling channel between the at least one of the hot section part or the cold section part and the corresponding cold section part or the corresponding hot section part.
    Type: Grant
    Filed: September 13, 2016
    Date of Patent: December 31, 2019
    Assignee: Rolls-Royce Corporation
    Inventor: Bruce Varney
  • Patent number: 10519777
    Abstract: The disclosure relates to a tip member configured to be coupled to a blade structure for a turbomachine. A body of the tip member includes: a first surface configured to engage a radially outboard end of the blade structure, a second surface positioned opposite the first surface, and at least one perimeter sidewall positioned between the first and second surfaces, wherein the at least one perimeter sidewall has an airfoil cross-section; and an opening passing through the body from the first surface to the second surface, and having a single directional orientation therebetween, wherein the opening is sized to receive a post positioned on the radially outboard end of the blade structure.
    Type: Grant
    Filed: May 14, 2018
    Date of Patent: December 31, 2019
    Assignee: General Electric Company
    Inventors: Travis J Packer, Jeffrey Clarence Jones, Nicholas William Rathay, Ian Darnall Reeves
  • Patent number: 10520193
    Abstract: The present application provides a cooling patch for use with a hot gas path component of a gas turbine engine. The cooling patch may include a base layer with a number of cooling channels extending therethrough, and a cover layer positioned on the base layer. The base layer and the cover layer may include a pre-sintered preform material.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: December 31, 2019
    Assignee: General Electric Company
    Inventor: Jonathan Dwight Berry
  • Patent number: 10370979
    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body defining a cavity, and a baffle including a baffle body including sidewalls and defining an internal passage for conveying coolant. The baffle body is situated in the cavity such that a majority of external surfaces of the sidewalls abut the cavity.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: August 6, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Lane Thornton
  • Patent number: 10358939
    Abstract: A gas turbine engine includes a body and a turbine-vane ring coupled to the body. The turbine-vane ring includes a plurality of turbine-vane assemblies. Each turbine-vane assembly includes a vane unit and a heat shield configured to reduce heat transfer to the vane unit from hot exhaust gases during operation of the gas turbine engine.
    Type: Grant
    Filed: March 2, 2016
    Date of Patent: July 23, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, Aaron D. Sippel, Tara G. Schetzel, David J. Thomas, Jun Shi, Brad D. Belcher
  • Patent number: 10196902
    Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.
    Type: Grant
    Filed: September 15, 2015
    Date of Patent: February 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sasha M. Moore, Timothy J. Jennings, Thomas N. Slavens, Clifford J. Musto, Nicholas M. LoRicco, Carey Clum, John McBrien, Christopher Whitfield, San Quach
  • Patent number: 10196910
    Abstract: A turbine vane for use in a gas turbine engine is disclosed. The turbine vane includes an inner platform, an outer platform spaced from the inner platform, and an airfoil that extends from the inner platform to the outer platform. The airfoil includes a ceramic-containing web that forms a portion of the airfoil and a metallic load shield that forms another portion of the airfoil.
    Type: Grant
    Filed: January 27, 2016
    Date of Patent: February 5, 2019
    Assignee: Rolls-Royce Corporation
    Inventor: Aaron P. Jennings
  • Patent number: 10024182
    Abstract: A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.
    Type: Grant
    Filed: January 24, 2014
    Date of Patent: July 17, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Paul Jenkinson, Mike McKenna
  • Patent number: 9920634
    Abstract: One embodiment of the present invention is a unique method of manufacturing a component for a turbomachine, such as an airfoil. Another embodiment is a unique airfoil. Yet another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for cooled gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: June 27, 2014
    Date of Patent: March 20, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Richard Christopher Uskert, Ted Joseph Freeman, David John Thomas, Jay E. Lane, Adam Lee Chamberlain, John Alan Weaver
  • Patent number: 9765635
    Abstract: An erosion and corrosion resistant protective coating for turbomachinery application includes at least one ceramic or metal-ceramic coating segment deposited on surface of a conductive metal substrate subjected to a pre-deposition treatment by at least blasting to provide the surface with texture. The erosion and corrosion resistant coating has a plurality of dome-like structures with dome width between in range from about 0.01 ?m to about 30 ?m. The at least one coating segment is formed by condensation of ion bombardment from a metal-gaseous plasma flow, wherein, at least during deposition of first micron of the coating segment, deposition rate of metal ions is at least 3 ?m/hr and kinetic energy of deposited metal ions exceeds 5 eV.
    Type: Grant
    Filed: August 11, 2016
    Date of Patent: September 19, 2017
    Assignee: Nano-Product Engineering, LLC.
    Inventor: Vladimir Gorokhovsky
  • Patent number: 9696035
    Abstract: A method for making shaped cooling holes in a substrate by pulsing and stopping a laser while moving the laser or substrate. The method produces shaped cooling holes with a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension.
    Type: Grant
    Filed: May 1, 2013
    Date of Patent: July 4, 2017
    Assignee: General Electric Company
    Inventors: John Howard Starkweather, William Bennett, John Gibbons, Anthony Urbanski
  • Patent number: 9598979
    Abstract: A method for producing a diffusion cooling hole extending between a wall having a first wall surface and a second wall surface includes forming a cooling hole inlet at the first wall surface, forming a cooling hole outlet at the second wall surface, forming a metering section downstream from the inlet and forming a multi-lobed diffusing section between the metering section and the outlet. The inlet, outlet, metering section and multi-lobed diffusing section are formed by laser drilling, particle beam machining, fluid jet guided laser machining, mechanical machining, masking and combinations thereof.
    Type: Grant
    Filed: July 9, 2012
    Date of Patent: March 21, 2017
    Assignee: United Technologies Corporation
    Inventors: Gordon Miller Reed, Paul R. Faughnan, Jr., John Quitter
  • Patent number: 9562437
    Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
    Type: Grant
    Filed: April 26, 2013
    Date of Patent: February 7, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel C. Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
  • Patent number: 9546553
    Abstract: The film cooling structure includes: a wall surface along which a heating medium flows; and at least one pair of film cooling holes that open at the wall surface and that blow a cooling medium. The pair of film cooling holes are arranged to be adjacent to each other in a main flow direction of the heating medium. In addition, perforation directions of the pair of film cooling holes are set such that directions of swirls of the cooling medium formed by blowing are opposite to each other, a swirl of the cooling medium on a downstream side in the main flow direction is mixed and merged with another swirl of the cooling medium on an upstream side in the main flow direction, and the merged cooling medium flows along the wall surface in a direction intersecting with the main flow direction.
    Type: Grant
    Filed: April 30, 2014
    Date of Patent: January 17, 2017
    Assignee: IHI CORPORATION
    Inventors: Yoji Okita, Chiyuki Nakamata, Seiji Kubo, Osamu Watanabe
  • Patent number: 9482108
    Abstract: Embodiments of the present disclosure include a system comprising a turbomachine blade assembly having a blade portion, a shank portion, and a mounting portion, wherein the blade portion, the shank portion, and the mounting portion comprise a first plurality of plies extending from a tip of the airfoil to a base of the dovetail.
    Type: Grant
    Filed: April 3, 2013
    Date of Patent: November 1, 2016
    Assignee: General Electric Company
    Inventor: Andres Jose Garcia Crespo
  • Patent number: 9429027
    Abstract: An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: August 30, 2016
    Assignee: United Technologies Corporation
    Inventors: Dominic J. Mongillo, Jr., Steven Bruce Gautschi, San Quach
  • Patent number: 9297261
    Abstract: An airfoil for a turbine engine, the airfoil including a first side wall, a second side wall spaced apart from the first side wall, and an internal cooling channel formed between the first side wall and the second side wall. The internal cooling channel includes at least one pedestal having a first pedestal end connected to the first side wall and a second pedestal end connected to the second side wall. The internal cooling channel also includes a first fillet disposed around the periphery of the first pedestal end between the first side wall and the first pedestal end; and a second fillet disposed around the periphery of the second pedestal end between the second side wall and the second pedestal end. At least one of the first fillet and the second fillet includes a profile that is non-uniform around the periphery of the corresponding pedestal end.
    Type: Grant
    Filed: March 7, 2012
    Date of Patent: March 29, 2016
    Assignee: United Technologies Corporation
    Inventor: Edwin Otero
  • Patent number: 9228437
    Abstract: An air cooled turbine blade with a trailing edge cooling circuit that is formed by casting the airfoil with a pressure side trailing edge lip being oversized, and then machining away material from the pressure side wall to leave a pressure side bleed slot with a smaller (t/s) ratio than can be formed by casting alone. In another embodiment, the airfoil is cast with a trailing edge exit hole, and then the material on the pressure side wall in the trailing edge region is machined away to leave a pressure side bleed slot instead of an exit hole.
    Type: Grant
    Filed: March 22, 2012
    Date of Patent: January 5, 2016
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Patent number: 9145773
    Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to trailing edge. Each cooling hole includes an asymmetric flow cross section through one or more asymmetric intermediate sections leading into slot. Flow cross section is asymmetric with respect to a mid-plane extending axially and spanwise through intermediate sections. Different trailing edge cooling holes may include different asymmetric flow cross sections. Lands may extend between the cooling slots. A raised floor may extend away from at least one of pressure or suction sidewalls at least partially through one or more asymmetric intermediate sections and optionally at least partially through cooling slot. Raised floor may include up and down ramps and a flat transition section between ramps.
    Type: Grant
    Filed: May 14, 2012
    Date of Patent: September 29, 2015
    Assignee: General Electric Company
    Inventors: Robert Frederick Bergholz, Jr., Daniel Lee Durstock
  • Patent number: 9051842
    Abstract: A system includes a turbine blade, which includes at least one cooling slot configured to convey a coolant in a flow direction from an interior to an exterior of the turbine blade. The cooling slot includes an entrance coupled to the interior and a converging section downstream from the entrance. The converging section includes a first cross-sectional area that decreases in the flow direction. The cooling slot also includes an exit disposed along a trailing edge of the turbine blade.
    Type: Grant
    Filed: January 5, 2012
    Date of Patent: June 9, 2015
    Assignee: General Electric Company
    Inventors: Aaron Ezekiel Smith, Christopher Michael Penny
  • Patent number: 9033670
    Abstract: Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.
    Type: Grant
    Filed: April 11, 2012
    Date of Patent: May 19, 2015
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Don Mittendorf, David K. Jan, Jason Smoke, Amandine Miner
  • Patent number: 9029729
    Abstract: A process for reopening cooling-air holes by a laser in order to remove coat down is provided. A nanosecond laser is provided and used for reopening the holes, wherein pulse times between 1 ?s and 20 ?s and a pulse frequency between 20 kHz and 40 kHz provided by the nanosecond laser are used.
    Type: Grant
    Filed: December 13, 2012
    Date of Patent: May 12, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andrea Massa, Rolf Wilkenhöner, Adrian Wollnik
  • Publication number: 20150104326
    Abstract: A turbine rotor blade is provided for a turbine section of an engine. The turbine rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge; a tip cap extending between the first side wall and the second side wall; a first parapet wall extending from the first side wall; and a first cooling hole through the tip cap and the first parapet wall configured to deliver cooling air. The first cooling hole has a closed channel section and an open channel section. The open channel section forms a slot.
    Type: Application
    Filed: October 16, 2013
    Publication date: April 16, 2015
    Inventors: David Waldman, Mark C. Morris, Malak Fouad Malak
  • Patent number: 9003657
    Abstract: A manufacturing method includes providing a substrate with an outer surface and at least one interior space and machining the substrate to selectively remove a portion of the substrate and define one or more cooling supply holes therein. Each of the one or more cooling supply holes is in fluid communication with the at least one interior space. The method further includes disposing an open cell porous metallic layer on at least a portion of the substrate. The open cell porous metallic layer is in fluid communication with the one or more cooling supply holes. A coating layer is disposed on the open cell porous metallic layer. The coating layer having formed therein one or more cooling exit holes in fluid communication with the open cell porous metallic layer. The substrate, the one or more cooling supply holes, the open cell porous metallic layer and the cooling exit holes providing a cooling network for a component.
    Type: Grant
    Filed: December 18, 2012
    Date of Patent: April 14, 2015
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Scott Andrew Weaver, Wayne Charles Hasz
  • Publication number: 20150052751
    Abstract: A system for manufacturing an airfoil includes an unfocused laser beam and a first fluid column surrounding the unfocused laser beam to create a confined laser beam directed at the airfoil. A sensor inside the airfoil detects penetration of the confined laser beam through the surface of the airfoil. A method for manufacturing an airfoil includes confining an unfocused laser beam inside a first fluid column to create a confined laser beam, directing the confined laser beam at a surface of the airfoil, and penetrating the surface of the airfoil with the confined laser beam. The method further includes detecting penetration of the confined laser beam through the surface of the airfoil.
    Type: Application
    Filed: August 20, 2013
    Publication date: February 26, 2015
    Applicant: General Electric Company
    Inventors: Zhaoli Hu, Douglas Anthony Serieno, Mark Joel Kromer
  • Patent number: 8938879
    Abstract: A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: January 27, 2015
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Patent number: 8915713
    Abstract: The present application thus provides an airfoil for use in a turbine. The airfoil may include a wall, an internal cooling plenum, and a cooling hole extending through the wall to the cooling plenum. The cooling hole may include an offset counterbore therein.
    Type: Grant
    Filed: September 27, 2011
    Date of Patent: December 23, 2014
    Assignee: General Electric Company
    Inventor: Bradley Taylor Boyer
  • Patent number: 8914975
    Abstract: A method for repairing a guide blade segment fashioned as a twin guide blade segment within a guide blade composite element, the guide blades being formed from a nose segment and a rear edge segment, the method having identification, within a guide blade segment, of a non-repairable guide blade to be separated from the guide blade composite structure; separation of a non-repairable guide blade from a one repairable guide blade in a first plane of division; division of at least one separated guide blade in a second plane of division between the nose segment and the rear edge segment; reconditioning of the at least one repairable nose segment and/or rear edge segment; joining of a reconditioned and/or new nose segment to a reconditioned and/or new rear edge segment to form at least one guide blade; and joining of at least two guide blades to form a guide blade segment.
    Type: Grant
    Filed: July 13, 2007
    Date of Patent: December 23, 2014
    Assignee: MTU Aero Engines GmbH
    Inventor: Joachim Wulf
  • Patent number: 8910379
    Abstract: Methods of fabricating coated components using multiple types of fillers are provided. One method comprises forming one or more grooves in an outer surface of a substrate. Each groove has a base and extends at least partially along the outer surface of the substrate. The method further includes disposing a sacrificial filler within the groove(s), disposing a permanent filler over the sacrificial filler, disposing a coating over at least a portion of the substrate and over the permanent filler, and removing the first sacrificial filler from the groove(s), to define one or more channels for cooling the component. A component with a permanent filler is also provided.
    Type: Grant
    Filed: September 4, 2013
    Date of Patent: December 16, 2014
    Assignee: General Electric Company
    Inventors: Raul Basilio Rebak, Renee Bushey Rohling, Scott Andrew Weaver, Ronald Scott Bunker, Don Mark Lipkin, Lawrence Bernard Kool
  • Publication number: 20140356188
    Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.
    Type: Application
    Filed: April 26, 2013
    Publication date: December 4, 2014
    Applicant: HONEYWELL INTERNATIONAL, INC.
    Inventor: HONEYWELL INTERNATIONAL, INC.
  • Patent number: 8881397
    Abstract: A method for designing an air cooled turbine airfoil includes selecting a number of different internal cooling air circuits, forming a ceramic core for each of the different cooling air circuits, forming a metal airfoil over each of the ceramic cores, leaching away the ceramic cores, mounting the airfoils in a stage of a turbine, passing a hot gas stream through the turbine, passing cooling air through each of the airfoils, and measuring a pressure and temperature differential across each of the airfoils to determine which cooling air circuit has the best performance.
    Type: Grant
    Filed: October 16, 2012
    Date of Patent: November 11, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Adam R Dowd
  • Patent number: 8875393
    Abstract: A method for forming at least one cooling channel in a wall which is cooled by cool air flowing in the channel is provided. The channel includes a hole and a diffusion portion, the hole opening out at one end into the inside surface of the wall, and at its other end into the diffusion portion where it forms an orifice. The diffusion portion flares around the orifice and opens out into the outside surface of the wall. The diffusion portion has a bottom whose front end is substantially plane, sloping, and extending in front of the orifice, and also has a margin extending behind, round the sides, and in front of the orifice, the margin joining the sides of the front end.
    Type: Grant
    Filed: May 26, 2010
    Date of Patent: November 4, 2014
    Assignee: SNECMA
    Inventors: Emmanuel Pierre Camhi, Laurent Crouilbois, Jean Pierre Mareix, Didier Pasquiet
  • Patent number: 8857055
    Abstract: A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: October 14, 2014
    Assignee: General Electric Company
    Inventors: Bin Wei, Jon Conrad Schaeffer, Ronald Scott Bunker, Wenwu Zhang, Kathleen Blanche Morey, Jane Marie Lipkin, Benjamin Paul Lacy, Wilbur Douglas Scheidt
  • Publication number: 20140271225
    Abstract: A rotor blade comprising an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage.
    Type: Application
    Filed: January 9, 2013
    Publication date: September 18, 2014
    Applicant: General Electric Company
    Inventor: General Electric Company
  • Patent number: 8814518
    Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platform, wherein, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a pressure side of the platform comprises a topside extending circumferentially from the airfoil to a pressure side slashface. The platform cooling arrangement may include: a platform cavity formed within the pressure side of the platform, a high-pressure connector that connects the platform cavity to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform cavity to the low-pressure coolant region of the interior cooling passage; and a pin bank formed within the platform cavity that includes radial pins.
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: John Wesley Harris, Jr., Craig Allen Bielek, Scott Edmond Ellis, Xiaoyong Fu
  • Patent number: 8814517
    Abstract: In a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the airfoil and the root include an interior cooling passage formed therein, wherein, in operation, the interior cooling passage comprises at least a high-pressure coolant region and a low-pressure coolant region, platform cooling arrangement that includes: a platform slot extending circumferentially from a mouth formed through the pressure side slashface; a high-pressure connector that connects the platform slot to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform slot to the low-pressure coolant region of the interior cooling passage; and a platform cooling cartridge removably engaged within the platform slot, the platform cooling cartridge comprising one or more cartridge cooling channels.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventors: Scott Edmond Ellis, Xiaoyong Fu
  • Patent number: 8794921
    Abstract: A platform cooling arrangement for a turbine rotor blade having a platform and an interior cooling passage and, in operation, a high-pressure coolant region and a low-pressure coolant region, wherein the platform includes a topside, which extends from the airfoil to a pressure side slashface, and an underside. The platform cooling arrangement may include: an airfoil manifold that resides near the junction of the pressure face of the airfoil and the platform; a slashface manifold that resides near the pressure side slashface; a high-pressure connector that connects the airfoil manifold to a high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the slashface manifold to a low-pressure coolant region of the interior cooling passage; cooling apertures that extend from a starting point along the pressure side slashface to a connection with the airfoil manifold, bisecting the slashface manifold therebetween; and a plurality of non-integral plugs.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: August 5, 2014
    Assignee: General Electric Company
    Inventors: Scott Edmond Ellis, Daniel Alan Hynum
  • Patent number: 8777568
    Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that in operation, includes at least a high-pressure coolant region and a low-pressure coolant region, and wherein the platform includes a platform underside. The platform cooling arrangement may include: a plate that comprises a plate topside; a channel formed on the plate topside, the channel comprising an upstream end and a downstream end, and being open through the plate topside such that, upon attaching the plate to the platform, the platform underside comprises a channel ceiling; a high-pressure connector that connects the upstream end of the channel to the high-pressure coolant region of the interior cooling passage; and a low-pressure connector that connects the downstream end of the channel to the low-pressure coolant region of the interior cooling passage.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: July 15, 2014
    Assignee: General Electric Company
    Inventors: Scott Edmond Ellis, John Wesley Harris, Jr., Adrian Lional Scott
  • Publication number: 20140154096
    Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.
    Type: Application
    Filed: December 3, 2012
    Publication date: June 5, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel Cregg Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
  • Patent number: 8739404
    Abstract: The present disclosure is directed to the use and manufacture of cooling features within a component used in a hot gas path, such as within a turbine. In one embodiment, channels are formed within an external surface of the component and filled with a removable material. The external surface and channels may then be coated with one or more layers, such as a structural layer and/or top coat. The removable material may then be removed to leave the channels free of the removable material.
    Type: Grant
    Filed: November 23, 2010
    Date of Patent: June 3, 2014
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Bin Wei, Ann Melinda Ritter, Don Mark Lipkin, Raul Basilio Rebak, Lawrence Bernard Kool, Dennis Michael Gray
  • Patent number: 8733315
    Abstract: A soluble and substantially ring-shaped casting core may include a cooling channel in a piston having at least one inflow and at least one outflow. The casting core may form a closed ring and the inflow may be arranged directly adjacent to the outflow. The casting core may have a cross-sectional taper for forming a choke in the circumferential direction between the inflow and the outflow.
    Type: Grant
    Filed: May 24, 2012
    Date of Patent: May 27, 2014
    Assignee: Mahle International GmbH
    Inventors: Helmut Kollotzek, Thomas Hettich, Frank Ehmann
  • Publication number: 20140115892
    Abstract: Methods for testing turbine blades. One method for testing turbine blades includes measuring dimensions of each of a first set of turbine blades. The method also includes testing airflow through first openings in each of the first set of turbine blades to determine airflow properties of each of the first set of turbine blades. The method includes determining a relationship between the dimensions and the airflow properties of each of the first set of turbine blades. The method includes measuring dimensions of each of a second set of turbine blades. The method also includes determining airflow properties for each of the second set of turbine blades based at least partially on the dimensions of the second set of turbine blades and the relationship.
    Type: Application
    Filed: October 31, 2012
    Publication date: May 1, 2014
    Applicant: General Electric Company
    Inventors: Michelle Rene Bezdecny, Michael Evans Graham, Michael Lee Bartholomew
  • Patent number: 8704128
    Abstract: There are a multiplicity of methods of making through-holes. In particular in the production of a multiplicity of film-cooling holes, as in gas turbine blades or combustion chamber elements, small time advantages are also important when making a hole. The method according to the invention, to make the hole close to the final contour in each case in sections in a top and a bottom region in order to then produce the final contour with other laser parameters, achieves time advantages.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: April 22, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Thomas Beck, Nigel-Philip Cox, Silke Settegast
  • Publication number: 20140093387
    Abstract: A method of manufacturing a cooled turbine blade for use in a gas turbine engine. The method includes forming an inner blade pattern, the inner blade pattern including an inner spar and a plurality of inner spar cooling fins. The method also includes forming an inner blade core, removing the inner blade pattern from the inner blade core, forming an outer blade pattern, forming a casting shell, removing the outer blade pattern from the casting shell, and casting the cooled turbine blade in the casting shell. The method also includes removing the casting shell from the cast cooled turbine blade, and removing the inner blade core from the cast cooled turbine blade.
    Type: Application
    Filed: September 28, 2012
    Publication date: April 3, 2014
    Applicant: SOLAR TURBINES INCORPORATED
    Inventors: Stephen Edward Pointon, Andrew Meier, Nnawuihe Asonye Okpara, Daniel Martinez
  • Patent number: 8684664
    Abstract: A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: April 1, 2014
    Assignee: General Electric Company
    Inventors: John Wesley Harris, Jr., Scott Edmond Ellis, Xiaoyong Fu, Adrian Lional Scott
  • Publication number: 20140075755
    Abstract: A system for manufacturing an airfoil includes an outer surface of the airfoil, a cavity inside the airfoil, and a collimator outside of the airfoil. The system further includes a fluid column flowing from the collimator toward the outer surface of the airfoil, and a laser beam inside the fluid column creates a confined laser beam directed at the outer surface of the airfoil. A method for manufacturing an airfoil includes confining a laser beam inside a fluid column to create a confined laser beam, directing the confined laser beam at an outer surface of the airfoil, and creating a passage through the outer surface of the airfoil with the confined laser beam.
    Type: Application
    Filed: September 14, 2012
    Publication date: March 20, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Zhaoli Hu, Douglas Anthony Serieno, Peter Galen Stevens, Benjamin Erick Baker
  • Patent number: 8672613
    Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an exit region at the second surface. The second surface has a non-planar curvature in the vicinity of the exit region. The film cooling hole is tapered at the exit region, such that the curvature of the film cooling hole in the exit region conforms to the non-planar curvature of the second surface, thereby forming a curved exit region. A method is also provided for forming at least one film cooling hole in the component. The method includes forming a straight section in the component wall, such that the straight section extends through the first surface, and tapering the film cooling hole, such that the curvature of the film cooling hole in the exit region conforms to the non-planar curvature of the second surface, thereby forming a curved exit region for the film cooling hole.
    Type: Grant
    Filed: August 31, 2010
    Date of Patent: March 18, 2014
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker