Resilient Patents (Class 415/135)
  • Patent number: 11035244
    Abstract: Turbine engine turbine sealing module extending about an axis and including a distributor fixed to a casing, and at least one blade connected to an outer platform. The turbine module further includes an impeller mounted rotating inside the casing and surrounded by a sealing ring fastened to this casing. The sealing ring includes an annular row of ring sectors arranged such that the circumferential end edges of two adjacent sectors are facing one another. Each sector includes a body configured to engage with at least one seal lip carried by the impeller and a hook which extends circumferentially which is configured to engage with a fastening rail of the casing. Each ring sector further includes a deflector which extends radially inwards and upstream with respect to the axis, such that the radially inward end thereof extends around a downstream end of the outer platform of the distributor.
    Type: Grant
    Filed: July 1, 2019
    Date of Patent: June 15, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Simon Nicolas Morliere, Nicolas Jean-Marc Marcel Beauquin, Renaud James Martet, Vincent Francois Georges Millier
  • Patent number: 11015486
    Abstract: A gas turbine includes a housing; a rotor rotatable by a fluid flowing through the housing; a bearing for rotatably supporting the rotor; and a support structure configured to support the bearing with respect to the housing. The support structure includes an inner casing accommodating the bearing; an outer casing fastened to the housing; and a strut extending between the inner and outer casings, and at least one of the inner casing and the outer casing includes a diaphragm that is deformable in a radial direction of the rotor. Each casing includes a strut root connected to the strut, a strut platform surrounding the strut root and being formed as the diaphragm; and a main body surrounding the strut platform. Damage to the support structure due to thermal expansion can be prevented, and the support structure can be easily designed to avoid resonance between the support structure and the rotor.
    Type: Grant
    Filed: August 25, 2018
    Date of Patent: May 25, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Ja Won Seo
  • Patent number: 11008894
    Abstract: A clip for an air seal assembly, comprising a clip base having a control ring interface; a biasing element coupled to the clip base opposite the control ring interface; wherein the clip is insertable into a clip receiver and configured to engage a notch of a blade outer air seal and configured to detachably couple with a clip mounting flange.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: May 18, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Dean W. Johnson, Thomas E. Clark
  • Patent number: 10982558
    Abstract: Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.
    Type: Grant
    Filed: December 6, 2018
    Date of Patent: April 20, 2021
    Assignee: MTU AERO ENGINES AG
    Inventors: Vitalis Mairhanser, Stephen Royston Williams, Werner Humhauser
  • Patent number: 10982564
    Abstract: An apparatus and system for mechanically connecting components are provided. The apparatus includes a mechanical connecting joint that includes a first joint member formed of a material having a first coefficient of thermal expansion (CTE) value, the first joint member comprising a first sidewall, a second opposite sidewall, and a body extending therebetween. The mechanical connecting joint further includes a second joint member formed of a material having a second CTE value, the second CTE being less than the first CTE. The second joint member includes a first leg facing the first sidewall, a second leg facing the second sidewall, and a connecting member extending between the first leg and the second leg. A first gap is formed between the first joint member and the first leg and a second gap is formed between the first joint member and the second leg.
    Type: Grant
    Filed: March 19, 2018
    Date of Patent: April 20, 2021
    Inventors: Matthew Mark Weaver, Michael Alan Hile, Kathleen Elizabeth Albers
  • Patent number: 10865658
    Abstract: In a gas turbine exhaust member and an exhaust chamber maintenance method, the gas turbine exhaust member is provided with: an inside diffuser that forms a tubular shape and is divided into multiple parts in the circumferential direction; a first seal housing that forms a tubular shape and is integrally formed in the circumferential direction, the front end of which being coupled to the rear end of the inside diffuser; a second seal housing that forms a tubular shape and is integrally formed in the circumferential direction, the front end of which being coupled to the rear end of the first seal housing; and a supporting coupling part that supports the rear end of the first seal housing and the front end of the second seal housing so as to allow the rear end and the front end to move in the axial direction.
    Type: Grant
    Filed: July 3, 2015
    Date of Patent: December 15, 2020
    Assignee: MITSUBISHI POWER, LTD.
    Inventor: Shinya Hashimoto
  • Patent number: 10808553
    Abstract: Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: October 20, 2020
    Assignee: Rolls-Royce plc
    Inventors: Michael J. Whittle, Anthony Razzell
  • Patent number: 10801350
    Abstract: An actively cooled assembly adapted for use in a gas turbine engine is disclosed herein. In illustrative embodiments, the assembly includes at least one ceramic matrix composite component with an attachment feature.
    Type: Grant
    Filed: February 23, 2018
    Date of Patent: October 13, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Jeffrey A. Walston, Daniel K. Vetters
  • Patent number: 10738656
    Abstract: A sealing assembly for a gas turbine is provided, especially an aircraft gas turbine, including: a first component having a first flange portion and a second component having a second flange portion; in the area of the first flange portion and the second flange portion, the first component and the second component being detachably intercoupled by a bolt connection; between the first component, especially a rounded portion, and the second component, especially the second flange portion, a variable interspace being provided that is at least partially sealed by at least one sealing element. The sealing element has a first sealing portion that rests against the first component, especially against the rounded portion, and a second sealing portion that rests against the second component, especially against the second flange portion; the first sealing portion and the second sealing portion being interconnected and extending obliquely relative to each other.
    Type: Grant
    Filed: April 6, 2018
    Date of Patent: August 11, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Boeck
  • Patent number: 10718235
    Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of ceramic matrix composite material, each ring sector having a portion forming an annular base with an inside face defining the inside face of the turbine ring, and an outside face from which there extends a wall defining an internal housing in which a holder member made of metal material is present, the holder member being connected to the ring support structure and including a body from which elastically deformable holder elements extend inside the internal housing on either side of the body, the holder elements bearing against the wall.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: July 21, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clément Roussille, Thierry Tesson
  • Patent number: 10711637
    Abstract: A turbine component assembly is disclosed, including a first component, a second component, and an interface shield. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The interface shield is disposed on a contact region of the first component, and directly contacts the second component.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: July 14, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Glenn Curtis Taxacher, Bruce Badding, Herbert Chidsey Roberts, III
  • Patent number: 10662965
    Abstract: A sealing structure includes: an insertion hole formed in a sealing plate; a sealing ring provided in the insertion hole; a first rotating body provided to the shaft, at least a part of the first rotating body positioned inside the insertion hole; a second rotating body disposed at a position apart from the compressor impeller than the first rotating body and having a maximum outer diameter larger than a minimum inner diameter of the insertion hole; and an annular receiving groove formed by the first rotating body and the second rotating body and receiving an inner circumferential surface side of the sealing ring.
    Type: Grant
    Filed: December 14, 2017
    Date of Patent: May 26, 2020
    Assignee: IHI Corporation
    Inventors: Yoshiaki Hirai, Nobuyuki Ikeya, Kouta Kimachi
  • Patent number: 10605092
    Abstract: A gas turbine engine component having a cooling passage includes a first wall defining an inlet of the cooling passage, a second wall generally opposite the first wall and defining an outlet of the cooling passage, a metering section extending downstream from the inlet, and a diffusing section extending from the metering section to the outlet. The metering section includes an upstream side and a downstream side generally opposite the upstream side. At least one of the upstream and downstream sides includes a first passage wall and a second passage wall where the first and second passage walls intersect to form a V-shape.
    Type: Grant
    Filed: July 11, 2016
    Date of Patent: March 31, 2020
    Assignee: United Technologies Corporation
    Inventor: JinQuan Xu
  • Patent number: 10533437
    Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.
    Type: Grant
    Filed: October 31, 2014
    Date of Patent: January 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Timothy Dale, Swati G. Bhanderi
  • Patent number: 10502064
    Abstract: An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.
    Type: Grant
    Filed: August 7, 2017
    Date of Patent: December 10, 2019
    Assignee: United Technologies Corporation
    Inventors: Daniel A. Bales, Dmitri Novikov, Robert C. Dolan, Kenneth A. Frisk, Steven T. Gordon, William R. Graves, Eric W. Malmborg, Francis B. Parisi, Randy P. Salva, Michael A. Weisse, Russell A. Beers, Xuedong Zhou, Christopher Treese, Tri Nguyen
  • Patent number: 10436045
    Abstract: A support device supports an inner member of a fixed body including the inner member and an outer member, the inner member being arranged around a rotating body and divided into upper and lower sections and the outer member being arranged in at least a part around the inner member and divided into upper and lower sections.
    Type: Grant
    Filed: March 2, 2015
    Date of Patent: October 8, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventor: Shinya Honda
  • Patent number: 10344612
    Abstract: A section of a gas turbine engine includes a rotor blade designed to rotate about an axis. The section also includes a case positioned radially outward from the rotor blade and extending circumferentially about the axis. The section also includes a control ring being annular, positioned radially inward from the case and designed to move radially relative to the case. The section also includes a segmented blade outer air seal (BOAS) including a plurality of BOAS segments each being positioned radially outward from the rotor blade, movably coupled to the control ring, and designed to move circumferentially relative to each other such that a circumferential gap between each of the plurality of BOAS segments changes in size in response to a temperature change in the section of the gas turbine engine.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: July 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eric A. Hudson, Michael G. McCaffrey, Stanley J. Funk, Scott D. Virkler
  • Patent number: 10309257
    Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: June 4, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Richard C. Uskert, Peter J. Loftus, Andrew J. Lazur
  • Patent number: 10273818
    Abstract: A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.
    Type: Grant
    Filed: April 15, 2016
    Date of Patent: April 30, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jack D. Petty
  • Patent number: 10247041
    Abstract: A frame employed in a turbine exhaust case of a gas turbine engine includes a frame outer ring, a frame inner ring, and a plurality of frame struts that connect the frame outer ring to the frame inner ring. The frame outer ring includes a plurality of bosses disposed circumferentially around the frame outer ring, wherein at least one of the plurality of bosses includes a mounting surface that receives and secures a removable bracket to the frame outer ring that supports a weight of the frame.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventor: Jonathan Ariel Scott
  • Patent number: 10214872
    Abstract: The present invention provides a foundation for a wind turbine. To reduce set-up time and to allow complete alignment of the platform which carries the base flange of the tower construction, the invention provides a foundation with a cage structure having an upper stress distribution flange connected by a plurality of tensioned anchor bolts to a lower flange. The flanges are separated by a number of distance elements whereby the shape of the cage structure becomes fixed by the combination between tensioned bolts and distance elements. Since the cage structure has a fixed shape, the upper stress distribution flange can be aligned before the cage structure is embedded in concrete, and it becomes unnecessary to wait for the concrete to harden.
    Type: Grant
    Filed: April 14, 2015
    Date of Patent: February 26, 2019
    Assignee: Vestas Wind Systems A/S
    Inventor: Børge Øllgaard
  • Patent number: 10167877
    Abstract: An object of the present invention is to decrease a surging limit flow rate at a low flow rate time, by increasing the inflow velocity to the blade of the impeller wheel, by providing a resistive element that narrows in the radial direction a passage cross section of an air intake passage which communicates between a impeller wheel of a centrifugal compressor and an air intake opening. The centrifugal compressor includes: the compressor housing 9 having the air intake opening 13 opened in a rotary shaft direction, and the air intake passage 11; and the impeller wheel 7 for compressing the air flowing in from the air intake opening 13, inside the housing.
    Type: Grant
    Filed: February 22, 2013
    Date of Patent: January 1, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Seiichi Ibaraki, Isao Tomita, Hiroshi Suzuki
  • Patent number: 10167737
    Abstract: A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide vane into a corresponding plurality of openings defined in the bulkhead for bearing circumferential loads.
    Type: Grant
    Filed: March 12, 2013
    Date of Patent: January 1, 2019
    Assignee: United Technologies Corporation
    Inventors: Gregory E. Reinhardt, Paul Thomas Rembish, Steven L. Conner, Thomas B. Hyatt, Steven J. Feigleson, Carl Brian Klinetob
  • Patent number: 10138750
    Abstract: A seal assembly includes a seal arc segment defining first and second seal supports with a carriage defining first and second support members. The first support member supports the seal arc segment in a first ramped interface, and the second support member supports the seal arc segment in a second ramped interface. A spring is configured to bias the seal arc segment axially. A heat shield is radially inward of the spring.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: November 27, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, Benjamin F. Hagan, David Richard Griffin
  • Patent number: 10132177
    Abstract: A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: November 20, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Fribourg, Pierre Delaleau, Florian Tellier
  • Patent number: 10107129
    Abstract: A seal assembly includes a seal arc segment that has first and second seal supports. A carriage has first and second support members. The first support member supports the seal arc segment in a first ramped interface and the second support member supports the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. First and second opposed springs bias the seal arc segment toward a circumferential default position.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: October 23, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 10054000
    Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterized in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.
    Type: Grant
    Filed: August 1, 2014
    Date of Patent: August 21, 2018
    Assignee: SNECMA
    Inventors: Fabrice Marcel Noel Garin, Florence Valerie Bon, Jerome Etienne Robert Cameau, Jean-Marc Michel Lesaine, Alain Paul Madec
  • Patent number: 10041369
    Abstract: This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) having at least one attachment hook adjacent one of a leading edge and a trailing edge thereof. The BOAS further includes at least one radial standoff axially aligned with the at least one attachment hook.
    Type: Grant
    Filed: August 5, 2014
    Date of Patent: August 7, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Brian R. Pelletier, James N. Knapp
  • Patent number: 10041364
    Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: August 7, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
  • Patent number: 10036269
    Abstract: A gas turbine sealing assembly includes a first static gas turbine wall, a second static gas turbine wall, and a leaf seal having a first side and a second side. The first static gas turbine wall contacts the second side at a first position, and the second static gas turbine wall contacts the second side at a second position. A spring exerts force on the first side. The spring includes a first spring wall coupled to the first static gas turbine wall. A second spring wall extends radially outward from the first spring wall. A third spring wall extends axially away from the second spring wall. A fourth spring wall extends radially inward from the third spring wall and includes a radially inner end. The radially inner end of the fourth spring wall contacts the first side of the leaf seal between the first position and the second position.
    Type: Grant
    Filed: October 23, 2015
    Date of Patent: July 31, 2018
    Assignee: General Electric Company
    Inventors: Johnnattan Tennessee Ugarte, Darrell Glenn Senile, Mullahalli Venkataramaniah Srinivas, Jonathon Farmer, Hugh Quill
  • Patent number: 10006341
    Abstract: A compressor assembly is disclosed. The compressor assembly may have a compressor housing. The compressor assembly may also have a compressor impeller disposed within the compressor housing. Further, the compressor assembly may have a bearing housing attached to the compressor housing. The compressor assembly may also have a diffuser ring disposed between the compressor housing and the bearing housing. In addition, the compressor assembly may have at least one tab. The tab may extend radially outward from the diffuser ring. The tab may be configured to engage with a recess in the compressor housing. The compressor assembly may also have at least one fastener. The fastener may be configured to attach the diffuser ring and the compressor housing.
    Type: Grant
    Filed: March 9, 2015
    Date of Patent: June 26, 2018
    Assignee: Caterpillar Inc.
    Inventors: Richard E. Annati, Robert C. Lancaster, David R. Adair
  • Patent number: 9988939
    Abstract: A fixed vane-type turbocharger is provided with a fixed vane in a conduit between a bearing housing and a turbine housing. The fixed vane is configured by a movable member disposed on one of the mutually opposing front faces of the bearing housing and the turbine housing so as to be capable of forward and backward movement, and by vanes which are fixed to the front face of the movable member. A pressing member presses the movable member so that the distal ends of the vanes are brought into pressure contact between the rear face of the movable member and either the bearing housing or the turbine housing with the other opposing front face of these. The pressing member contacts the rear face of the movable member within a range in the radial direction where the vanes are disposed, and presses within this range.
    Type: Grant
    Filed: September 12, 2011
    Date of Patent: June 5, 2018
    Assignee: IHI CORPORATION
    Inventor: Mikito Ishii
  • Patent number: 9970310
    Abstract: An assembled ring shroud is provided. The assembled ring shroud may comprise a cover, a first ring layer, a key layer, and a second ring layer. The cover may operatively wrap around, contain, and secure the first ring layer, the key layer, and the second ring layer. The key layer may comprise a key that may act for position and anti-rotation. The key layer may comprise spacers to hold the keys in place. The first ring layer and the second ring layer may be configured to provide further strength and support to the assembled ring shroud.
    Type: Grant
    Filed: January 21, 2016
    Date of Patent: May 15, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael McCaffrey
  • Patent number: 9856746
    Abstract: A gas turbine engine includes a service line interface that extends from an outer surface of a bearing support such that a heat shield is spaced from the outer surface. A method of mounting a heat shield to a gas turbine engine includes trapping a heat shield within a gapped overlap spaced from an outer surface of a bearing support.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: January 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Gary L Grogg, Grace E Szymanski
  • Patent number: 9726044
    Abstract: A method of assembling a gas turbine engine includes locating a consumable assembly tool clip within the engine.
    Type: Grant
    Filed: February 12, 2014
    Date of Patent: August 8, 2017
    Assignee: United Technologies Corporation
    Inventors: Michael S. Stevens, Timothy M. Davis
  • Patent number: 9551238
    Abstract: A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open.
    Type: Grant
    Filed: December 21, 2012
    Date of Patent: January 24, 2017
    Assignee: United Technologies Corporation
    Inventors: Hoyt Y. Chang, Shelton O. Duelm
  • Patent number: 9546572
    Abstract: A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall. The first attachment flange defines a first aperture and the second attachment flange defines a second aperture. A pin extends through the first aperture and into the second aperture.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: January 17, 2017
    Assignee: General Electric Company
    Inventors: Khoa Dang Cao, Kenneth Damon Black
  • Patent number: 9500130
    Abstract: A centerline support bar for steam turbine component assembly, installation, and/or alignment is disclosed. In one embodiment, the support bar includes a body portion configured to be disposed across a centerline of a steam turbine, the body portion configured to transversely connect to a steam turbine component; and a first flange extending from the body portion and configured to contact a steam turbine casing, wherein the steam turbine support bar is configured to non-affixedly join the steam turbine casing to the steam turbine component.
    Type: Grant
    Filed: March 5, 2013
    Date of Patent: November 22, 2016
    Assignee: General Electric Company
    Inventors: Stephen Roger Swan, Matthew Edward Renninger, Kevin John Lewis Roy, Prashant Prabhakar Sankolli
  • Patent number: 9488063
    Abstract: A clearance control system for a rotary machine includes an outer casing including an outer casing main portion having a first radial thickness, wherein the outer casing is configured to expand at a first time rate of thermal expansion. Also included is an inner casing disposed between the outer casing and a rotary portion, the inner casing including an inner casing main portion having a second radial thickness that is less than the first radial thickness, wherein the inner casing is configured to expand at a second time rate of thermal expansion that is greater than the first time rate of thermal expansion of the outer casing. Further included is an inner casing leg configured to separate from an outer casing leg during expansion of the inner casing and configured to engage the outer casing leg during contraction of the inner casing.
    Type: Grant
    Filed: September 12, 2013
    Date of Patent: November 8, 2016
    Assignee: General Electric Company
    Inventors: David Martin Johnson, Radu Ioan Danescu
  • Patent number: 9359907
    Abstract: A stationary blade cascade 29 of an embodiment includes stationary blade structures 50 and a ring-shaped support structure 40 supporting the stationary blade structures 50. The stationary blade structures 50 each include: a stationary blade part 51 where steam passes; and an outer circumference side constituent part 52 formed on an outer circumference side of the stationary blade part 51 and having a fitting groove 56 which penetrates all along a circumferential direction and which has an opening 55 all along the circumferential direction in a downstream end surface 54 of the outer circumference side constituent part 52. The support structure 40 includes a ring-shaped support part 42 having a fitting portion 41 fitted in the fitting grooves 56 of the outer circumference side constituent parts 52. The plural stationary blade structures 50 are supported along the circumferential direction by the ring-shaped support part 42.
    Type: Grant
    Filed: November 28, 2012
    Date of Patent: June 7, 2016
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Tsuguhisa Tashima, Itaru Murakami, Motoki Yoshikawa
  • Patent number: 9353649
    Abstract: A wear liner for a stator vane includes a shaped member, comprising a U-shaped portion that receives a foot of a stator vane. A first end of the wear liner is biased into contact with the stator vane. A spring seal extends from the U-shaped portion and into bias contact with an inner surface of the support structure to further prevent leakage between the stator foot and case support structure.
    Type: Grant
    Filed: January 8, 2013
    Date of Patent: May 31, 2016
    Assignee: United Technologies Corporation
    Inventor: Philip Robert Rioux
  • Patent number: 9347456
    Abstract: A non-metallic vertical turbine pump and a method of manufacturing same are provided. In accordance with one embodiment, the vertical turbine pump can include a motor, and a drive shaft coupled to the motor for rotation, a casing with a mixed flow diffuser including a diffuser hub and diffuser vanes that project out from the diffuser hub, and a mixed flow impeller configured to rotatably fit inside the casing, having an impeller hub, impeller vanes, extending from the hub, and a front and a back shroud connected to opposing ends of the impeller vanes. At least one of the mixed flow impeller and the mixed flow diffuser can be made of a non-metallic material and is a singular homogenous component.
    Type: Grant
    Filed: August 17, 2011
    Date of Patent: May 24, 2016
    Assignee: MPC, Inc.
    Inventors: William W. Parry, Erik Burachinsky
  • Patent number: 9303531
    Abstract: A quick engine change assembly, comprises a first circular frame member, a plurality of doublet supports spaced about the first circular frame member, the doublet supports being contoured along the axial direction, a flow surface defined between the plurality of doublet supports and, a plurality of cradles, each of the cradles including the doublet supports, the doublet supports from a lower portion of the cradle to the flow surface.
    Type: Grant
    Filed: October 16, 2012
    Date of Patent: April 5, 2016
    Assignee: General Electric Company
    Inventors: William Howard Hasting, Courtney James Tudor
  • Patent number: 9273563
    Abstract: An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.
    Type: Grant
    Filed: August 14, 2012
    Date of Patent: March 1, 2016
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W. Norris
  • Patent number: 9074478
    Abstract: A damped assembly within a gas turbine, comprising a first member and a second member mechanically connected via an intermediate vibration dampener which has at least first and second surfaces for contacting the first and second members respectively, wherein either or both of the first and second surfaces include a plurality of raised portions in direct contact with the respective member and a plurality of recessed portions which contain adhesive for bonding the intermediate vibration dampener to the respective member.
    Type: Grant
    Filed: August 11, 2011
    Date of Patent: July 7, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Eric P. Ravey, Matthew D. Curren
  • Patent number: 8974891
    Abstract: Methods of forming ceramic matrix composite structures include joining at least two lamina together to form a flexible ceramic matrix composite structure. Ceramic matrix composite structures include at least one region of reduced inter-laminar bonding at a selected location between lamina thereof. Thermal protection systems include at least one seal comprising a ceramic matrix composite material and have at least one region of reduced inter-laminar bonding at a selected location between lamina used to form the seal. Methods of forming thermal protection systems include providing one or more such seals between adjacent panels of a thermal protection system.
    Type: Grant
    Filed: October 26, 2007
    Date of Patent: March 10, 2015
    Assignee: COI Ceramics, Inc.
    Inventor: James A. Riedell
  • Patent number: 8961116
    Abstract: An exhaust plenum for connection to an exhaust outlet portion of a gas turbine for receiving turbine exhaust gas. The exhaust plenum includes a first wall. The first wall includes a seal attachment component in thermal contact with an exterior shell of the first wall and is adapted for attaching an annular flex seal to the first wall. The seal attachment component extends generally around a perimeter of the inlet of the exhaust plenum, and is thermally insulated from an interior space of the exhaust plenum.
    Type: Grant
    Filed: May 22, 2012
    Date of Patent: February 24, 2015
    Assignee: Braden Manufacturing, LLC
    Inventors: Laquinnia Lawson, Jr., Stephen W. Bigham
  • Publication number: 20150050127
    Abstract: A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.
    Type: Application
    Filed: June 16, 2014
    Publication date: February 19, 2015
    Inventors: Christopher J. Peters, Daniel R. Bowers
  • Publication number: 20150016956
    Abstract: One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.
    Type: Application
    Filed: December 28, 2013
    Publication date: January 15, 2015
    Inventors: Richard C. Uskert, David J. Thomas, Adam L. Chamberlain
  • Publication number: 20140314547
    Abstract: A first ceramic matrix composite structure having a first flange with a first aperture, and a second structure having a second flange with a second aperture are clamped together by a fastener and spring assembly. The second flange is in contact with the first flange and the apertures of the first and second flanges align with each other. A threaded fastener having a thermal expansion rate that is different than the thermal expansion rate of at least one of the first ceramic matrix composite structure and second structure extends through the aligned apertures. The fastener includes a bolt, a nut, and a spring assembly that maintains a constant clamping pressure irrespective of the thermal expansion differences between the bolt and the first ceramic matrix composite structure and second structure.
    Type: Application
    Filed: August 31, 2012
    Publication date: October 23, 2014
    Applicant: United Technologies Corporation
    Inventors: David J. Sander, Shelton O. Duelm