Passage Contains Tubular Insert Patents (Class 29/889.722)
  • Patent number: 10724387
    Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, a first shear tube may extend through the airfoil and relatively orthogonal to the first platform and the second platform, wherein the first shear tube extends through the first platform and the second platform. In various embodiments, a second shear tube may extend through the airfoil into the first platform and the second platform parallel the first shear tube.
    Type: Grant
    Filed: November 8, 2018
    Date of Patent: July 28, 2020
    Inventors: Bryan H. Farrar, Howard J. Liles, Michael G McCaffrey, Andrew J. Lazur
  • Patent number: 10677091
    Abstract: An airfoil includes a supply passage to provide a coolant, an airfoil section that has walls that define an internal cavity, a baffle seated in the internal cavity, and a seal proximate the edge of the baffle. The baffle is seated such that there is a gap between the baffle and at least one of the walls. The baffle includes a baffle wall that has cooling holes and that defines an interior baffle region. The seal seals off the gap such that the coolant that exits the supply passage will be directed to flow into the interior baffle region.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: June 9, 2020
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10294800
    Abstract: A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: May 21, 2019
    Inventors: Emanuele Facchinetti, Guillaume Wagner, Marc Henze
  • Patent number: 9974296
    Abstract: The application is generally directed towards an airfoil for a fluid delivery tube. The airfoil includes a securing member operably connecting the airfoil to the tube, a fin extending downward and outward from the securing member and terminating in a tip, a shield extending inward and downward from the tip of the fin, and an air guide extending from a first end of the shield.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: May 22, 2018
    Inventors: Joe V. Gednalske, William Thomas Hambleton, Eric P. Spandl, Lillian C. Magidow, Gregory Dahl, Laura J. Hennemann
  • Patent number: 9650899
    Abstract: A turbine assembly includes a basically hollow aerofoil. A wall segment may be arranged at a side of the aerofoil. An insertion aperture in the wall segment provides access to the aerofoil and an impingement tube may be inserted via the insertion aperture into the aerofoil to be located within the aerofoil and extend at least in a span wise direction of the aerofoil. A protrusion section of the impingement tube may extend in a direction basically perpendicular to the span wise direction over an edge of the insertion aperture. The protrusion section may be overlapped by at least a part of the wall segment. Adjacent to the protrusion section, an overlap section of the impingement tube is arranged to abut the edge of the insertion aperture. The protrusion section and the overlap section may be formed integrally with each other in one piece.
    Type: Grant
    Filed: June 11, 2012
    Date of Patent: May 16, 2017
    Inventor: Jonathan Mugglestone
  • Publication number: 20150104322
    Abstract: A thermal management article, a method for forming a thermal management article and a thermal management method are disclosed. Forming a thermal management article includes forming a duct adapted to be inserted into a groove on the surface of a substrate, and attaching the duct to the groove so that the top outer surface of the duct is substantially flush with the surface of the substrate. Thermal management of a substrate includes transporting a fluid through the duct of a thermal management article to alter the temperature of the substrate.
    Type: Application
    Filed: October 15, 2013
    Publication date: April 16, 2015
    Inventors: David Edward SCHICK, Srikanth Chandrudu Kottilingam, Benjamin Paul Lacy, Yan Cui, Brian Lee Tollison
  • Patent number: 8689440
    Abstract: A method of forming a hollow component with an internal structure from first and second panels includes the step of forming at least one protrusion on a surface of at least one of the first and second panels by a material deposition process. The first and second panels are assembled into a preform the panels being oriented such that each panel defines an interior and an exterior facing surface, with the at least one protrusion extending from an exterior facing surface of a panel. The preform is expanded against a die, such that the at least one protrusion is transferred from the exterior surface of a panel to the interior surface of a panel so as to define an internal structure. Forming the at least one protrusion may include encapsulating an elongate member on the surface of a panel by a material deposition process.
    Type: Grant
    Filed: January 18, 2011
    Date of Patent: April 8, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Oliver Michael Strother, Dean Gwynfryn Jones
  • Patent number: 8591191
    Abstract: A film cooling hole for a turbine airfoil having a diffusion section with a convergent wall and two divergent side walls, and with a thin exit slot that opens onto the airfoil surface. The divergent side walls have an expansion of 15 to 25 degrees and the convergent wall converges up to 15 degrees. The film hole is formed by an electrode than is pushed into the metal surface to form the divergent side walls and then pivoted to form the convergent wall.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: November 26, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Patent number: 8496440
    Abstract: A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing a metallic plate for forming the aerofoil structure; joining mounting elements to opposing end surfaces of said metallic plate; dividing said plate along a plane extending substantially in a span-wise direction so as to produce two metallic panels each with one of said mounting elements joined thereto; assembling the two metallic panels so that the surfaces of the panels opposite to the surfaces which have been divided are facing each other; and joining the two metallic panels to one another to form the aerofoil structure; wherein the mounting elements are joined to one another to form the root of the aerofoil.
    Type: Grant
    Filed: February 9, 2010
    Date of Patent: July 30, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Michael J. Wallis
  • Patent number: 8458886
    Abstract: A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing for an insert is machined in a metal body having an upper face; an insert formed from a fiber bundle having a metal matrix is placed in the housing; a metal cover is placed on the metal body so as to cover the insert; the cover is welded onto the metal body; the assembly including the metal body with the cover undergoes a hot isostatic compression treatment; and the treated assembly is machined to obtain the part. The insert is a rectilinear insert and the housing forms a rectilinear groove that extends beyond the insert and is open at each end, the groove being filled by a tab when the cover is placed on the metal body.
    Type: Grant
    Filed: December 24, 2008
    Date of Patent: June 11, 2013
    Assignee: Messier-Bugatti-Dowty
    Inventors: Richard Masson, Dominique Ducos
  • Patent number: 8453327
    Abstract: Fabricating a turbine component (50) by casting a core structure (30), forming an array of pits (24) in an outer surface (32) of the core structure, depositing a transient liquid phase (TLP) material (40) on the outer surface of the core structure, the TLP containing a melting-point depressant, depositing a skin (42) on the outer surface of the core structure over the TLP material, and heating the assembly, thus forming both a diffusion bond and a mechanical interlock between the skin and the core structure. The heating diffuses the melting-point depressant away from the interface. Subsurface cooling channels (35) may be formed by forming grooves (34) in the outer surface of the core structure, filling the grooves with a fugitive filler (36), depositing and bonding the skin (42), then removing the fugitive material.
    Type: Grant
    Filed: February 5, 2010
    Date of Patent: June 4, 2013
    Assignee: Siemens Energy, Inc.
    Inventor: David B. Allen
  • Patent number: 8382439
    Abstract: A turbine rotor blade made from the spar and shell construction in which the shell is a thin wall shell made from a high temperature resistant material that is formed by a wire EDM process, and where the shell is secured to the spar using a retainer that is poured into retainer occupying spaces formed in the shell and the spar, and then hardened to form a rigid retainer to secure the shell to the spar. The spar and the shell both have grooves facing each other to form a retainer groove. A retaining material, such as a liquid or a powdered metal, is poured into the grooves and hardened to form a retainer to secure the shell to the spar. The retaining material also forms a seal on the top of the spar and between the spar and shell.
    Type: Grant
    Filed: September 24, 2011
    Date of Patent: February 26, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Wesley D Brown
  • Publication number: 20120134845
    Abstract: A blade (30?) for a gas turbine has an airfoil (31) and a blade root (32) for mounting the blade (30) on a rotor shaft of the gas turbine. The airfoil (31) is provided with cooling channels (33, 35) in the interior thereof, which cooling channels (33, 35) preferably extend along the longitudinal direction and can be supplied with cooling air (45) through cooling air supply passages (40-43() within the blade root (32). The blade root (32) includes a blade channel (40) running transversely through the blade root (32) and is connected to the cooling channels (33, 35), and an insert (41) is inserted into the blade channel (40) for determining the final configuration and characteristics of the connections between the blade channel (40) and the cooling channels (33, 35).
    Type: Application
    Filed: November 29, 2011
    Publication date: May 31, 2012
    Inventor: Alexander Anatolievich KHANIN
  • Patent number: 7798773
    Abstract: A method of repairing a vane segment for a gas turbine engine includes removing an engine-run cooling baffle from the vane segment, forming a non-engine-run manufacturing detail that includes an inner platform, an outer platform, and an airfoil, attaching the engine-run cooling baffle to the non-engine-run manufacturing detail, and marking the non-engine-run manufacturing detail with a serial number associated with the vane segment from which the engine-run cooling baffle was removed.
    Type: Grant
    Filed: August 6, 2007
    Date of Patent: September 21, 2010
    Assignee: United Technologies Corporation
    Inventors: Paul M. Pellet, David J. Hiskes, Orville L. Dunn
  • Publication number: 20100221098
    Abstract: A turbine component has an airfoil portion with at least one central core element, a pressure side wall, and a suction side wall. The airfoil portion also has a serpentine cooling passageway in at least one of the walls. In a preferred embodiment, the airfoil portion has a serpentine cooling passageway in both of the pressure and suction side walls. A refractory metal core for forming the serpentine cooling passageway(s) is also described.
    Type: Application
    Filed: May 14, 2010
    Publication date: September 2, 2010
    Inventors: Frank Cunha, William Abdel-Messeh
  • Publication number: 20100034662
    Abstract: An airfoil component having a body having a leading edge and a trailing edge, a ceramic casting insert for making the component and the method for making the component. The component includes an internal cooling passageway and an elongated opening in communication with the internal cooling passageway. The opening is configured with a geometry that provides structural stability during casting and has a cross-section that sufficiently restricts airflow through the opening to provide efficient component operation. The casting insert includes outer edge projections and a web portion corresponding to the geometry of the openings when cast around the insert. The method includes casting the airfoil component around the casting insert and removing the insert to provide the component having the openings.
    Type: Application
    Filed: December 26, 2006
    Publication date: February 11, 2010
    Inventors: Richard W. Jendrix, Cory Williams
  • Patent number: 7540083
    Abstract: Methods are provided for modifying an airfoil internal cooling circuit that include a flow path configured to direct air through the airfoil in a direction and the airfoil having a leading edge, a trailing edge, and a first and a second wall therebetween, each wall having an inner and an outer surface, the inner surfaces defining a cavity and having features forming at least a portion of the internal cooling circuit. The methods may include the steps of forming a pilot hole through the airfoil first and second walls at a predetermined location, forming an insert hole based on the predetermined location, the insert hole enveloping the pilot hole and configured to receive at least a portion of an insert configured to modify the internal cooling circuit flow path, placing the insert into the insert hole, and bonding the insert to the airfoil first and second walls.
    Type: Grant
    Filed: September 28, 2005
    Date of Patent: June 2, 2009
    Assignee: Honeywell International Inc.
    Inventors: Mark C. Morris, Jason C. Smoke, William J. Weidner, Craig A. Wilson, Edward J. Mayer
  • Patent number: 7410342
    Abstract: A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer surface, in which a plurality of hoop fibers are secured within a resin matrix to firmly secure the metallic insert to the ceramic airfoil body. Axial loads between the insert and the ceramic body are transferred to the hoop fibers. The hoop fibers are strong enough to resist extending in length that would permit the hoop fibers from sliding over the widest portion of the insert.
    Type: Grant
    Filed: August 18, 2005
    Date of Patent: August 12, 2008
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Alfred P. Matheny
  • Patent number: 7121796
    Abstract: A cooling insert/nozzle assembly for use in gas turbines or similar machinery includes a nozzle having inner and outer ribs with cast-in “T” sections and “L” sections, respectively, at the end of the ribs in which air flow enters the nozzle. The assembly further includes a cooling insert having a flexible end which is inserted between adjacent ribs having either the cast-in “T” or “L” sections.
    Type: Grant
    Filed: April 30, 2004
    Date of Patent: October 17, 2006
    Assignee: General Electric Company
    Inventors: Steven S. Burdgick, Gary M. Itzel
  • Patent number: 7093359
    Abstract: A method of manufacturing a composite structure uses a layer of an insulating material (22) as a mold for forming a substrate of a ceramic matrix composite (CMC) material (24). The insulating material may be formed in the shape of a cylinder (10) with the CMC material wound on an outer surface (14) of the cylinder to form a gas turbine combustor liner (20). Alternatively, the insulating material may be formed in the shape of an airfoil section (32) with the CMC material formed on an inside surface (36) of the insulating material. The airfoil section may be formed of a plurality of halves (42, 44) to facilitate the lay-up of the CMC material onto an easily accessible surface, with the halves then joined together to form the complete composite airfoil. In another embodiment, a box structure (102) defining a hot gas flow passage (98) is manufactured by forming insulating material in the shape of opposed airfoil halves (104) joined at respective opposed ends by platform members (109).
    Type: Grant
    Filed: September 17, 2002
    Date of Patent: August 22, 2006
    Assignee: Siemens Westinghouse Power Corporation
    Inventors: Jay A. Morrison, Gary Brian Merrill, Jay Edgar Lane, Steven C. Butner, Harry A. Albrecht, Scott M. Widrig, Yevgeniy P. Shteyman
  • Patent number: 6986644
    Abstract: Methods of producing impeller castings from very hard materials are disclosed in which the formation of a selectively configured core produces an impeller casting that does not need to be machined to receive the drive shaft and eliminates the need for employing a lead babbitt or soft insert, as is known in the prior art, to receive the drive shaft, thereby producing a hard material impeller for a centrifugal pump that is significantly less costly to produce and is environmentally safe.
    Type: Grant
    Filed: May 2, 2003
    Date of Patent: January 17, 2006
    Assignee: Envirotech Pumpsystems, Inc.
    Inventor: James Shaw
  • Patent number: 6742984
    Abstract: A pair of hollow elongated leg sections are disposed in one or more of the nozzle vane cavities of a nozzle stage of a gas turbine. Each leg section has an outer wall portion with apertures for impingement-cooling of nozzle wall portions in registration with the outer wall portions. The leg sections may be installed into the cavity separately and support rods support and maintain the leg sections in spaced relation, whereby the designed impingement gap between the outer wall portions of the leg sections and the nozzle wall portions is achieved. The support rods are secured to the inner wall portions of the leg sections by welding or brazing.
    Type: Grant
    Filed: May 19, 2003
    Date of Patent: June 1, 2004
    Assignee: General Electric Company
    Inventors: Gary Michael Itzel, Robert Henry Devine, II, John Alan Eastman
  • Patent number: 6610385
    Abstract: A component formed at least in part by a CMC material and equipped with an integrally-formed surface feature, such as an airflow enhancement feature in the form of a turbulator or flow guide. The CMC material comprises multiple sets of tows woven together to form a preform that is infiltrated with a matrix material. The surface feature is integrally defined at a surface of the cooling passage by an insert member disposed between adjacent tows of at least one of the tow sets. The insert member has a cross-sectional size larger than the adjacent tows, forming a protrusion in the preform that defines the surface feature in the infiltrated, consolidated and cured CMC material.
    Type: Grant
    Filed: December 20, 2001
    Date of Patent: August 26, 2003
    Assignee: General Electric Company
    Inventor: Ronald Ralph Cairo
  • Patent number: 6539627
    Abstract: A component for use in a flow path of a gas turbine engine. The component includes a body having an exterior surface mountable in the gas turbine engine so the exterior surface is exposed to gases flowing through the flow path of the engine. The body has a cooling hole extending through the body to the exterior surface for transporting cooling air from a cooling air source outside the flow path of the engine to the exterior surface of the body for providing a layer of cooling air adjacent the exterior surface of the body to cool the surface and create a thermal barrier between the exterior surface and the gases flowing through the flow path of the gas turbine engine. The cooling hole is defined by an elongate annular surface extending through the body of the component and terminating at the exterior surface of the body. The hole has a length, a maximum width less than about 0.
    Type: Grant
    Filed: February 7, 2002
    Date of Patent: April 1, 2003
    Assignee: General Electric Company
    Inventor: James N. Fleck
  • Patent number: 6453557
    Abstract: An insert containing apertures for impingement cooling a nozzle vane of a nozzle segment in a gas turbine is inserted into one end of the vane. The leading end of the insert is positioned slightly past a rib adjacent the opposite end of the vane through which the insert is inserted. The end of the insert is formed or swaged into conformance with the inner margin of the rib. The insert is then brazed or welded to the rib.
    Type: Grant
    Filed: April 11, 2000
    Date of Patent: September 24, 2002
    Assignee: General Electric Company
    Inventor: Steven Sebastian Burdgick
  • Patent number: 6339879
    Abstract: A method for accurately sizing and forming the cooling holes of an air-cooled gas turbine engine component on which a protective diffusion coating will be deposited. The method generally entails drilling a hole in a surface region of a substrate, and then measuring the thickness of any recast surface region surrounding the hole and created as a result of a portion of the surface region having melted and then resolidified. The thickness of the additive layer of the diffusion coating that will deposit on a corresponding recast surface region of the component is then predicted based on an inverse relationship determined to exist with the thickness of the recast surface region formed during drilling of the cooling hole. An appropriately-oversized hole can then be formed in the component so that, after depositing the diffusion coating on the component, the additive layer grows sufficiently within the hole to yield a cooling hole approximately having the required final diameter.
    Type: Grant
    Filed: August 29, 2000
    Date of Patent: January 22, 2002
    Assignee: General Electric Company
    Inventors: Gary Eugene Wheat, Terri Kay Brown, Thomas Phillip Schumacher
  • Patent number: 6265022
    Abstract: Process of plugging cooling holes (4) of a gas turbine component (1) with an external surface (7), having a cavity (2) and a plurality of cooling holes (4) before coating the gas turbine component (4), characterised in that mask material (6) is applied to the external surface (7) of the component (1) while a fluid is forced through the cooling holes (4), the mask material (6) is thickened while the fluid is forced through the cooling holes (4), the cooling holes (4) are plugged with plug material (6b), the mask material (6a) is removed from the external surface (7) of the component (1), the component (1) and the plugged cooling holes (4) are coated and the plug material (6b) is removed from the cooling holes (4).
    Type: Grant
    Filed: July 14, 2000
    Date of Patent: July 24, 2001
    Assignee: ABB Alstom Power (Schweiz) AG
    Inventors: John Fernihough, Alexander Beeck, Andreas Bögli
  • Patent number: 6227801
    Abstract: A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and over a high work turbine blade at a lower static pressure than the diverted air to cool the blade. Advantageously, as the diverted air is relatively cool, use of a conventional TOBI nozzle may be eliminated. Similarly, showerheads on the blade may be eliminated. As well, the diverted air may conveniently be used to seal a rear bearing compartment within the engine.
    Type: Grant
    Filed: April 27, 1999
    Date of Patent: May 8, 2001
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Xiaoliu Liu
  • Patent number: 6193465
    Abstract: A gas turbine engine airfoil is manufactured by forming an internal retention seat in two complementary airfoil parts. An insert is fabricated for retention in the seat. The two parts are assembled with the insert disposed in the seat therebetween. The parts are then bonded together to trap the insert therein to collectively define the airfoil. The insert and seat may be precisely fabricated for improving the efficiency of the airfoil.
    Type: Grant
    Filed: September 28, 1998
    Date of Patent: February 27, 2001
    Assignee: General Electric Company
    Inventors: Gary C. Liotta, Paul J. Acquaviva, James N. Fleck