Specific Casing Or Vane Material Patents (Class 415/200)
  • Patent number: 8740558
    Abstract: An example composite fan case assembly includes a composite fan case body disposed on an axis. The fan case body has a radially inner surface and a radially outer surface. There is at least one mounting attachment to receive a threaded member. The at least one mounting attachment includes a base component and a spool component. The base component extends through an opening in the fan case body from the radially outer surface and toward the radially inner surface of the fan case body. The base component including a base portion, a boss having a non-cylindrical profile, and a cylindrical portion. The mounting attachment also includes a spool component disposed on the radially outer surface and attached to the base component. The spool component receives at least a portion of the base component. An outer surface of the cylindrical portion and an inner surface of the spool component are threaded and correspondingly mate to lock the spool component relative to the base component.
    Type: Grant
    Filed: April 29, 2011
    Date of Patent: June 3, 2014
    Assignee: United Technologies Corporation
    Inventors: Thomas J. Robertson, Jr., Darin S. Lussier
  • Patent number: 8740546
    Abstract: A guide vane of a condensation turbine steam turbine is provided, wherein the guide vane includes a heating resistor. The guide vane includes fiber composite material at least in some regions. The heating resistor may be embodied as a heating wire or as a heating film. A condensation steam turbine having a guide vane as described above is also provided.
    Type: Grant
    Filed: April 29, 2009
    Date of Patent: June 3, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Christoph Ebert, Albert Langkamp, Markus Mantei
  • Patent number: 8734103
    Abstract: A method of repairing a flange of a casing for an airplane turboprop or turbojet, in which the flange includes at least one through hole for passing a bolt for fastening equipment, and the hole opens out in a face of the flange that is worn by friction against the equipment, disclosed. The method includes mounting a bearing member on the flange. The bearing member includes a radial wall covering the worn face of the flange. The wall includes a hole that comes into register with the hole in the flange and having thickness for compensating the wear of the face of the flange. The member further includes an abutment for bearing against the periphery of the flange, and being fastened to the flange by adhesive.
    Type: Grant
    Filed: May 31, 2011
    Date of Patent: May 27, 2014
    Assignee: SNECMA
    Inventors: Patrick Jean-Louis Reghezza, Julien Tran
  • Patent number: 8734605
    Abstract: A composite component, such as an aerofoil component for a gas turbine engine, comprises a body and a platform which are formed from respective body and platform preforms. The body preform includes fibers which are directed laterally of the preform, forming a cavity in the end of the preform. The platform preform includes a projection constituting a deltoid filler which is received in the cavity. The projection includes a 3D woven structure of reinforcement fibers so that the cavity is occupied by fibers to give the platform a generally uniform volume fraction. A further platform preform fits over the body preform so that the lateral fibers are sandwiched between the platform preforms.
    Type: Grant
    Filed: November 30, 2009
    Date of Patent: May 27, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Neil R. Harrison
  • Patent number: 8734114
    Abstract: Blades for gas turbine engines which are formed from composite materials have problems with respect of resistance to impacts such as bird strikes. Previous blades formed from metals had some ductility towards the trailing edge which could accommodate the whiplash effects of impacts. With regard to composite materials such ductility is not present. By providing projections 32 which act as propagation wave trips as well as high intensity reflectors 36 it is possible to limit the whiplash at the edge 31 resulting in damage. Typically a cladding cap 38 is provided which also may be formed from a metal to allow some greater uniformity with respect to mass per length despite the tapering of the blade. Furthermore by providing voids which act as delamination initiation sites cracking can be provided between plies which allows greater flexibility towards the edge and therefore release of energy. These voids may incorporate uncured polymer matrix to act as a binder subsequent to delamination.
    Type: Grant
    Filed: June 3, 2008
    Date of Patent: May 27, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Alison J. McMillan
  • Publication number: 20140127005
    Abstract: A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fibre composite layer and/or a plastic component.
    Type: Application
    Filed: April 2, 2012
    Publication date: May 8, 2014
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD. & CO KG
    Inventor: Karl Schreiber
  • Patent number: 8714920
    Abstract: A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.
    Type: Grant
    Filed: April 1, 2010
    Date of Patent: May 6, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: Christian X. Campbell, Jay A. Morrison, Allister W. James, Raymond G. Snider, Daniel M. Eshak, John J. Marra, Brian J. Wessell
  • Publication number: 20140119905
    Abstract: A fan structure includes a casing, a fan, and two elastic members. The casing has an accommodation space. The fan is located in the accommodation space. The fan has a first side and a second side opposite to each other. One of the two elastic members is sandwiched between the casing and the first side of the fan. The other one of the two elastic members is sandwiched between the casing and the second side of the fan. The two elastic members normally keep the fan away from the casing, so as to make the fan contact the casing through the two elastic members, thereby achieving a damping effect.
    Type: Application
    Filed: March 7, 2013
    Publication date: May 1, 2014
    Applicants: INVENTEC CORPORATION, INVENTEC (PUDONG) TECHNOLOGY CORPORATION
    Inventors: Chun-Ming Lu, Wen-Cheng Hu, Chun-Ying Yang, Yen-Cheng Lin, Ming-Hung Shih, Ying-Chao Peng
  • Patent number: 8708659
    Abstract: A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.
    Type: Grant
    Filed: September 24, 2010
    Date of Patent: April 29, 2014
    Assignee: United Technologies Corporation
    Inventors: Brian S. Tryon, Darryl Stolz, Paul L. Reynolds, John J. Schirra
  • Publication number: 20140086734
    Abstract: A system and a method for making a composite containment casing are provided. The method includes providing a mandrel, applying at least one ply of a material about the mandrel to form a first annular facesheet, applying a plurality of core segments surrounding the first facesheet, forming a casing surrounding the core segments. and curing the facesheet, core segments, and casing together forming a unitary composite containment casing.
    Type: Application
    Filed: September 21, 2012
    Publication date: March 27, 2014
    Applicant: General Electric Company
    Inventor: Ming Xie
  • Publication number: 20140086735
    Abstract: A louver blade comprises a blade body and a reinforcing member. The blade body is made of a plastic material, includes a first end portion and a second end portion opposite to the first end portion along a first axis, and is provided with two pivot connecting portions. Each of the pivot connecting portions is disposed on the first axis at a corresponding one of the first and second end portions and is adapted for pivotal connection with a louver frame to ensure accurate alignment when mounting. The reinforcing member is made of a metal material, is embedded in the blade body, and has an H-shaped cross section to enhance the structural strength of the louver blade.
    Type: Application
    Filed: January 23, 2013
    Publication date: March 27, 2014
    Applicant: TAICANG KINGFU PLASTIC MANUFACTURE CO., LTD.
    Inventor: Szu-Chang Huang
  • Patent number: 8672609
    Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.
    Type: Grant
    Filed: February 16, 2012
    Date of Patent: March 18, 2014
    Assignee: United Technologies Corporation
    Inventors: Darin S. Lussier, Thomas J. Robertson, Jr., Mark W. Costa, Sreenivasa R. Voleti, Rajiv A. Naik
  • Publication number: 20140072421
    Abstract: A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap.
    Type: Application
    Filed: September 7, 2012
    Publication date: March 13, 2014
    Inventor: Steven Clarkson
  • Patent number: 8668447
    Abstract: A steam turbine blade includes a coating film formed at least a portion of a surface of the steam turbine blade, the coating film containing a ceramic matrix and nanosheet particles dispersed in the ceramic matrix. The steam turbine blade is employed as one of stator blades or one of rotor blades in a steam turbine. The steam turbine includes a turbine rotor, the rotor blades implanted in the turbine rotor, the stator blades provided in an upstream side of the corresponding rotor blades, and a turbine casing supporting the stator blades and accommodating turbine rotor, the rotor blades and the stator blades. The steam turbine is also configured such that the rotor blades are paired with the corresponding stator blades to form turbine stages arranged in an axial direction of the turbine rotor, thereby forming steam paths.
    Type: Grant
    Filed: December 17, 2009
    Date of Patent: March 11, 2014
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Akio Sayano, Masashi Takahashi, Masahiro Saito, Kazuyoshi Nakajima, Jianshun Huang, Kazuhiko Mori
  • Patent number: 8668441
    Abstract: The nacelle of the invention includes an air-inlet front section, a middle section for encasing the fan of the turbofan (7) and a rear section including means for connection to a pylon to be connected to the rigid structure or an airplane. The rear section includes a structural framework (18) having at least one aerodynamic smoothing and acoustic panel (21). The acoustic panel (21) is secured on the structural framework (18) by floating or elastic fixation means so that said acoustic panel (21) can be deformed in a direction (31) essentially centrifugal and radial relative to the turbofan (7) in the presence of overpressure air (3) in the engine compartment.
    Type: Grant
    Filed: October 15, 2007
    Date of Patent: March 11, 2014
    Assignee: Aircelle
    Inventor: Guy Bernard Vauchel
  • Patent number: 8662838
    Abstract: A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream.
    Type: Grant
    Filed: September 3, 2009
    Date of Patent: March 4, 2014
    Assignee: SNECMA
    Inventors: Laurent Ferrer, Claude Marcel Mons
  • Patent number: 8662851
    Abstract: A method for joining a cast metal material blade ring and a metal material hub structure into a turbine rotor. One of the blade ring and the hub structure is mounted in a holder and the other is mounted in a rotation holder for being rotated. At least one of these mountings is heated, and then they are pressed together with a selected force while rotating to weld the ring interior wall and the disk side to form the assembled structure.
    Type: Grant
    Filed: November 9, 2012
    Date of Patent: March 4, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Said Izadi
  • Publication number: 20140050574
    Abstract: A ram air fan outer housing for directing air from a ram air fan rotor and air from a ram air bypass into a ram air fan outlet. The outer housing includes an outer cylinder and a plenum connected at a joint region. The outer cylinder is made of a laminate stacking sequence of at least four adjacent layers of plain-weave carbon-fiber fabric in an A-B-B-A sequence. The plenum is made of a laminate stacking sequence of at least eight adjacent plenum layers of plain-weave carbon-fiber fabric in an A-B-B-A-A-B-B-A sequence. The plenum is joined to the outer cylinder at a joint region, the joint region includes a transition section transitioning the laminate stacking sequence from the eight adjacent layers of the plenum walls to the four adjacent layers of the outer cylinder walls.
    Type: Application
    Filed: August 15, 2012
    Publication date: February 20, 2014
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Eric Chrabascz, Craig M. Beers
  • Publication number: 20140044532
    Abstract: Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicant: MTU AERO ENGINES AG
    Inventor: Karl-Hermann RICHTER
  • Patent number: 8647058
    Abstract: In a cementless pump for pumping molten metal, support structure is suspended above the molten metal. A motor is supported by the support structure. A shaft is fastened to the motor. An impeller is mounted to a lower end of the shaft. A refractory base is supported in the molten metal and includes at least one impeller chamber in which the impeller is rotated and at least one discharge passageway. The base includes through holes. Support posts are each fastened to the support structure and to the base. Refractory sleeves are each disposed in one of the through holes. Post fastening members fasten the lower ends of the posts to the base without cement. A portion of each of the post fastening members is located inside the refractory sleeve. Also featured is a method of replacing posts in a cementless pump for pumping molten metal.
    Type: Grant
    Filed: June 27, 2011
    Date of Patent: February 11, 2014
    Inventor: Bruno H. Thut
  • Patent number: 8636466
    Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: January 28, 2014
    Assignee: Techspace Aero S.A.
    Inventor: Jean-François Cortequisse
  • Publication number: 20140023492
    Abstract: A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a static engine structure housing a compressor section, a combustor section and a turbine section. The core engine is configured to receive core airflow. A fan is arranged within the metallic fan containment case. The fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements.
    Type: Application
    Filed: July 23, 2012
    Publication date: January 23, 2014
    Inventor: James L. Lucas
  • Patent number: 8628302
    Abstract: An impeller comprising: a top shroud; a bottom shroud, a plurality of vanes extending from the top shroud to the bottom shroud, each said vane including a top edge at a radially inner portion of the vane in contact with the top shroud and a bottom edge at a radially outer portion of the vane in contact with the bottom shroud, such that a radially inner portion of the vane at the bottom edge of each vane is not in contact with or adjacent the bottom shroud and a radially outer portion of the vane at the top edge of each vane is not in contact with or adjacent the top shroud.
    Type: Grant
    Filed: June 25, 2012
    Date of Patent: January 14, 2014
    Assignee: Resmed Motor Technologies Inc.
    Inventors: Barton John Kenyon, Nicholas Jerome Reed, Andrew Wilson, Ian Michael Smith
  • Patent number: 8616847
    Abstract: A squealer tip preform having a coating including an abrasive is disclosed. The squealer tip may be separately formed from a generally elongated blade to which the squealer tip preform is configured to be attached. The squealer tip may be configured such that an outer surface of the squealer tip preform is generally aligned with an outer side surface of the turbine blade defining a cross-sectional profile of the turbine blade. Forming the squealer tip preform with an abrasive coating separate from the turbine blade greatly reduces costs and improves efficiency as compared with conventional systems.
    Type: Grant
    Filed: August 30, 2010
    Date of Patent: December 31, 2013
    Assignee: Siemens Energy, Inc.
    Inventor: David B. Allen
  • Patent number: 8616853
    Abstract: A method of fabricating a guide vane. The method produces a fiber preform by 3D weaving a single piece, the preform including a first portion extending along the longitudinal axis and constituting the preform for an airfoil of the vane, and at a longitudinal end of the first portion, a second portion constituting the preform for the platform of the vane, the second portion being produced as a first layer and a second layer facing the first layer and separated from the first layer by unlinking without cutting while producing the preform; folding the first and second layers such that each of them lies in a plane perpendicular to the longitudinal axis, substantially symmetrically to each other relative to the first portion, and such that a first region of the first layer covers a second region of the second layer in front of a front edge of the first portion; conforming the preform in a mold; and densifying the preform with a polymer matrix.
    Type: Grant
    Filed: July 9, 2009
    Date of Patent: December 31, 2013
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jean Noel Mahieu, Xavier Millier
  • Publication number: 20130343884
    Abstract: An impeller of a cooling fan includes a metal base, a shaft and a plurality of plastic blades. The metal base includes a shaft-coupling portion, a first assembling portion apart from the shaft-coupling portion, and a flat portion between the shaft-coupling portion and the first assembling portion, wherein the flat portion oppositely has a first flat surface and a second flat surface, and a permanent magnet is mounted on the first flat surface. The shaft has a fixing end coupled with the shaft-coupling portion of the metal base. Each of the plastic blades has a second assembling portion coupled with the first assembling portion of the metal base.
    Type: Application
    Filed: January 22, 2013
    Publication date: December 26, 2013
    Applicant: Sunonwealth Electric Machine Industry Co., Ltd.
    Inventor: Alex Horng
  • Patent number: 8613590
    Abstract: An article of manufacture has a body formed in part of a first metal alloy and in part of a second metal alloy, the second metal alloy having a thermal coefficient of expansion that is less than the thermal coefficient of expansion of the first metal alloy. A BOAS segment for a gas turbine engine is disclosed wherein the formation of cracks due to thermal mechanical fatigue in the body of the disclosed BOAS segment is minimized, if not eliminated, through a unique construction of the disclosed BOAS segment, whether original equipment manufacture or a repaired blade outer air seal. A method for manufacture of a BOAS segment and a method for modifying a BOAS segment are disclosed.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: December 24, 2013
    Assignee: United Technologies Corporation
    Inventors: Philip R. Belanger, Susan M. Tholen
  • Publication number: 20130336773
    Abstract: A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.
    Type: Application
    Filed: June 19, 2012
    Publication date: December 19, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Robertson, Darin S. Lussier, Mark W. Costa
  • Patent number: 8607577
    Abstract: An assembly for use in a gas turbine engine has an underlying metal sheet, and at least one ceramic matrix composite tile attached to the underlying metal sheet with at least one fastener assembly. The panel fastener assembly includes a fastener having a threaded portion extending rearwardly from a head, which has a frustoconical surface facing the threaded portion. The frustoconical surface is received in a frustoconical bore in the ceramic matrix composite panel. A bushing is positioned on an opposed side of the metal sheet from the ceramic matrix composite panel. The bushing has a flange extending away from the metal sheet. A sleeve is received about the threaded portion of the fastener, and extends away from the panel, beyond the metal sheet. The sleeve has a lip extending radially outwardly toward the flange on the bushing, such that the flange on the bushing extends beyond a space defined between the lip and a seating surface on the bushing. A wave spring is received within the cavity.
    Type: Grant
    Filed: November 24, 2009
    Date of Patent: December 17, 2013
    Assignee: United Technologies Corporation
    Inventors: Jose E. Ruberte Sanchez, Mitchell Aaron Riccione, Jocelyn Charis Glispin
  • Publication number: 20130323040
    Abstract: A centrifugal blowing fan includes a back yoke made from metal, having a substantially bottomed cylindrical portion around a rotating shaft of a motor, an inner surface attached with a magnet of the motor mounted thereon and a flange portion disposed around a periphery of an opening of the cylindrical portion; and a cylindrical impeller made from resin, having a plurality of blades circumferentially arranged, an annular collar portion joined with first ends of the plurality of blades and a doughnut-shaped disk portion joined with second ends of the plurality of blades, wherein the disk portion has at least one fitting, and the flange portion has at least one fitted space receiving the at least one fitting so as to concentrically and fixedly connect the impeller and the back yoke.
    Type: Application
    Filed: May 28, 2013
    Publication date: December 5, 2013
    Applicant: MINEBEA CO., LTD.
    Inventor: Kazuhiko FUJITA
  • Patent number: 8596972
    Abstract: A duct includes first and second composite duct sections and first and second metallic support ring sections. The second metallic support ring section is adjacent to the first metallic support ring section.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: December 3, 2013
    Assignee: United Technologies Corporation
    Inventor: Francis R. Moon
  • Publication number: 20130309062
    Abstract: Embodiments related to wind turbines and methods of guiding a flow of a fluid using a wind turbine. In one embodiment, a wind turbine includes a framework including an annular upper guide means and an annular base guide means; and an annular rotor assembly surrounding a central space, the rotor assembly comprising a plurality of rotor vanes, each rotor vane being held in position between the upper guide means and the base guide means.
    Type: Application
    Filed: July 19, 2013
    Publication date: November 21, 2013
    Inventor: Guy Andrew VAZ
  • Publication number: 20130309076
    Abstract: A rotating body of a vacuum pump is partially constituted by a fiber-reinforced plastic and configured to exhaust gas by rotation. A corrosion-resistant layer is provided on the fiber-reinforced plastic portion which is the base material of the rotating body. A high-emissivity layer having a higher emissivity than the corrosion-resistant layer is provided on the corrosion-resistant layer. Fixed members facing the rotating body of the vacuum pump are each provided with a high-emissivity layer having a higher emissivity than the base material of the fixed members on the surfaces facing the fiber-reinforced plastic portion of the rotating body.
    Type: Application
    Filed: November 28, 2011
    Publication date: November 21, 2013
    Applicant: Edwards Japan Limited
    Inventor: Manabu Nonaka
  • Patent number: 8584356
    Abstract: A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising: making a fiber preform (100) out of refractory fibers and having a shape corresponding to the shape of the lobed structure to be fabricated, from a plurality of component elements of fiber texture that are assembled together and shaped by means of tooling of a shape corresponding to the shape of the lobed structure to be fabricated so as to obtain an assembled fiber preform having a first preform portion (111) corresponding to the annular portion of the lobed structure and a second preform portion (112) corresponding to the multilobed skirt of the lobed structure, the component elements of the fiber preform being assembled together at least in part along connection lines (121) extending substantially in the flow direction of the flow past the lobes of the multilobed skirt preform portion; and densifying the assembled an
    Type: Grant
    Filed: February 11, 2008
    Date of Patent: November 19, 2013
    Assignee: Snecma Propulsion Solide
    Inventors: Eric Philippe, Jean-Daniel Lalanne, Pascal Ducharlet, Dominique Coupe
  • Publication number: 20130302154
    Abstract: A containment case for a gas turbine including: a cylindrical outer casing extending about an axis and having a radially outer and a radially inner surface; a coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing; and an array of ribs extending radially from the inner skin towards the axis. The case for can have the coaxially arranged cylindrical inner skin formed of a harder material than the outer casing joined to the inner surface of the cylindrical outer casing by a galvanic isolation layer.
    Type: Application
    Filed: April 29, 2013
    Publication date: November 14, 2013
    Applicant: ROLLS-ROYCE PLC
    Inventor: James Alex FINLAYSON
  • Publication number: 20130302153
    Abstract: An air circulation fan used in a light steel frame includes a top base, a circuit assembly, a shroud, a driving source, and a blade set. A pivoting portion of the shroud is pivotally connected to a combining portion of the top base, so that the shroud can pivotally hung on the top base. When the shroud is combined with the top base, the two connecting portions of the shroud are inserted into two through-holes of an accommodating casing with a second elastic piece of each through-hole abutting against a first elastic piece of each combining portion, thereby electrically connecting the circuit assembly to the driving source. When the shroud is separated from the top base, the connecting portions are removed from the through-holes with the second elastic piece being separated from the first elastic piece, thereby shutting off the electrical connection between the circuit assembly and the driving source.
    Type: Application
    Filed: May 10, 2012
    Publication date: November 14, 2013
    Inventor: Ching-Wen Liu
  • Patent number: 8579585
    Abstract: An inlet duct, an induction system, and a system are disclosed for directing an inlet flow into an inlet compressor for use in an internal combustion engine. An example inlet duct may include one or more relief features disposed on an inner surface of the inlet duct. The one or more relief features may be made integral with the inlet duct. The one or more relief features may be disposed to protrude into the inlet flow to cause the inlet flow to swirl before reaching the inlet compressor.
    Type: Grant
    Filed: May 14, 2012
    Date of Patent: November 12, 2013
    Assignee: Ford Global Technologies, LLC
    Inventors: Eric Henry Hermann, Randall Alan Stec, Douglas White, Jacqueline Tomlin, William C. Ronzi, Roger Khami, Robert Bruce Bonhard, Bhaskara Rao Boddakayala
  • Patent number: 8573949
    Abstract: A method and system that includes generation of an energy beam. The energy beam may be generated from a focused energy source. Additionally, the energy beam may be directed towards a pre-sintered preform. The pre-sintered preform may be made of a braze material and may seal a hole that may be located in a turbine component.
    Type: Grant
    Filed: September 30, 2009
    Date of Patent: November 5, 2013
    Assignee: General Electric Company
    Inventors: Yan Cui, Srikanth Chandrudu Kottilingam, Gene Murphy
  • Patent number: 8568093
    Abstract: A multi-stage centrifugal pump assembly which is manufactured in the same construction type with cast components on the one hand, and with a stainless steel lining formed of sheet metal on the other hand, includes a bearing carrier (13) which is designed and suitable for the connection of a cast housing component (12) as well as for receiving a sheet metal lining made of stainless steel.
    Type: Grant
    Filed: March 10, 2010
    Date of Patent: October 29, 2013
    Assignee: Grundfos Management a/s
    Inventor: Esben Brun Grønborg
  • Publication number: 20130272862
    Abstract: A method for manufacturing a fan blade includes the steps of, firstly, providing a mold. Then a mixture of metal powder and adhesive material is injected into the mold to forming a green body of the blade. Next, the adhesive material is removed from the green body of the blade. Finally, the green body of the blade is sintered to form the fan blade. A fan with such blades is also provided.
    Type: Application
    Filed: June 25, 2012
    Publication date: October 17, 2013
    Applicant: FOXCONN TECHNOLOGY CO., LTD.
    Inventor: MING-HSIU CHUNG
  • Patent number: 8545167
    Abstract: A gas turbine engine includes a fan including a plurality of circumferentially spaced rotatable blades, and a fan casing for containing fragments of fan blades in the event of blade release, the fan casing having a shell surrounding the blades and circumscribing a containment zone of the fan. The shell is made of a fiber reinforced polymer composite material which includes nanoparticles.
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: October 1, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Kin-Leung Cheung
  • Publication number: 20130251515
    Abstract: A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.
    Type: Application
    Filed: March 20, 2012
    Publication date: September 26, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Donald Earl Floyd, David Martin Johnson
  • Patent number: 8535000
    Abstract: A centrifugal pump is provided having a volute casing having a discharge conduit, an impeller provided in the volute casing, and a suction sideliner enclosing the impeller in the volute casing, the suction sideliner being at least partially covered with sintered tungsten carbide tiles. In one embodiment, the impellor has a central hub, a plurality of vanes spacedly attached to the hub, and at least one side plate attached to the vanes, whereby each vane is individually wear protected prior to attaching each vane to the hub.
    Type: Grant
    Filed: April 23, 2010
    Date of Patent: September 17, 2013
    Assignee: Syncrude Canada Ltd.
    Inventor: Stefano Chiovelli
  • Patent number: 8535001
    Abstract: The invention relates to a rotor wheel constructed of sheet metal for a centrifugal pump, particularly a multi-stage centrifugal pump, with means for fastening to the drive shaft of an electric motor, wherein the rotor wheel has a central coaxial opening in which a sleeve is fastened coaxially, wherein the sleeve projects out of the rotor wheel on at least one side of the rotor wheel, and wherein the sleeve has, in its inner wall, projecting, axially parallel ridges for fastening into axially parallel notches or grooves of the motor drive shaft.
    Type: Grant
    Filed: January 19, 2009
    Date of Patent: September 17, 2013
    Assignee: Wilo AG
    Inventor: Laurent Costaouec
  • Publication number: 20130236302
    Abstract: A method and system for protecting the rotor blade tips of rotary machines, particularly the compressors of gas turbine engines, comprising a rotor assembly having a plurality of circumferentially spaced-apart rotor blades, with each blade extending radially outwardly from an inner wheel disk; a stator assembly comprising one or more rows of spaced-apart vanes extending between adjacent rows of the rotor blades; a casing extending circumferentially around the rotor and stator assemblies; and an abradable ceramic coating applied to selected areas of the interior cylindrical surface of the rotor casing to thereby provide a minimum clearance between the casing and rotor blades during start up and to thereafter ensure an effective compressor seal for compressed gas flow.
    Type: Application
    Filed: March 12, 2012
    Publication date: September 12, 2013
    Inventors: Charles Alexander Smith, John David Memmer, Tushar Sharadchandra Desai
  • Patent number: 8528339
    Abstract: A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.
    Type: Grant
    Filed: April 5, 2007
    Date of Patent: September 10, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Jay A. Morrison, Gary B. Merrill, Daniel George Thompson, Steven James Vance
  • Publication number: 20130224005
    Abstract: A seal for a turbine casing is provided. The turbine casing includes a plurality of sections joined at flanges provided on each section. Each flange includes a bore and a counterbore. The seal comprises a compression sleeve seal having a length that is greater than a counterbore-to-counterbore length of two flanges; a fastener configured to extend through the compression sleeve seal; and a nut threadable on each end of the fastener. The compression sleeve seal is compressible between each flange and each nut to create a first seal and is radially extensible to create a second seal against each bore.
    Type: Application
    Filed: February 28, 2012
    Publication date: August 29, 2013
    Inventors: Matthew Stephen Casavant, Brett Darrick Klingler
  • Publication number: 20130216368
    Abstract: In accordance with an exemplary embodiment, a turbine stator component includes a first endwall; a second endwall; a first stator airfoil coupled between the first and second endwalls; and a second stator airfoil adjacent to the first airfoil and coupled between the first and second endwalls. The first stator airfoil has first crystallographic primary and secondary orientations. The second stator airfoil has second crystallographic primary and secondary orientations, the first crystallographic primary and secondary orientations being different from the second crystallographic primary and secondary orientations.
    Type: Application
    Filed: May 6, 2013
    Publication date: August 22, 2013
    Applicant: Honeywell International Inc.
    Inventor: Honeywell International Inc.
  • Publication number: 20130216367
    Abstract: A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.
    Type: Application
    Filed: February 16, 2012
    Publication date: August 22, 2013
    Inventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, JR., Christopher M. Quinn
  • Patent number: 8511980
    Abstract: A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The gas path portion comprises a forward portion forming a leading edge of a stationary vane, an aft portion forming a trailing edge of the stationary vane, and a plurality of middle portions forming a pressure side and a suction side of the stationary vane. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates.
    Type: Grant
    Filed: July 23, 2012
    Date of Patent: August 20, 2013
    Assignee: United Technologies Corporation
    Inventors: Tracy A. Propheter-Hinckley, Jun Shi