Between Blade Supported Radial Tip Ring And Static Part Patents (Class 415/173.6)
  • Patent number: 10655471
    Abstract: A flow path width at a hub endwall of a blade main body decreases toward a minimum width from a leading edge, and increases toward a trailing edge from the minimum width, the flow path width at a reference blade height aparted toward a tip side from the hub endwall of the blade main body gradually decreases toward the trailing edge from the leading edge, and an axial chord length position of the minimum flow path widths at respective blade height shift toward a transition to the trailing edge side from the hub endwall toward the tip side of the blade main body and coincides with the trailing edge at the reference blade height.
    Type: Grant
    Filed: February 10, 2016
    Date of Patent: May 19, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Koichiro Iida, Norifumi Hirata
  • Patent number: 10584714
    Abstract: A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.
    Type: Grant
    Filed: November 14, 2017
    Date of Patent: March 10, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jason Husband, James Glaspey
  • Patent number: 10514102
    Abstract: A gas turbine engine includes a first rotor shaft and a second rotor shaft around the first rotor shaft. A knife edge seal is radially between the first rotor shaft and the second rotor shaft, and is connected to one of the first rotor shaft or the second rotor shaft. The knife edge seal is sized radially to form a gap between the knife edge seal and the other of the first rotor shaft or the second rotor shaft. A plurality of blades having a general airfoil shape is between the first rotor shaft and the second rotor shaft proximate the knife edge seal. The plurality of blades is connected to the first rotor shaft or the second rotor shaft, and a second gap is formed radially between the plurality of blades and the other of the first rotor shaft or the second rotor shaft.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: December 24, 2019
    Assignee: United Technologies Corporation
    Inventor: Eric J. Ward
  • Patent number: 10495114
    Abstract: A blower fan includes a plurality of blades radially extending from a boss provided at a rotary center and spaced apart from each other in the rotational direction, and a ring portion connecting outer peripheral ends of the blades in a ring shape. A radially outer end part at an end on an air-flow upstream side of the ring portion is positioned outward in a radial direction of a rotary shaft in the blower fan, as toward the air-flow upstream side. Thus, the blower can prevent the backflow air from being swirled, thereby reducing noise.
    Type: Grant
    Filed: February 20, 2015
    Date of Patent: December 3, 2019
    Assignee: DENSO CORPORATION
    Inventors: Toshikatsu Kondou, Youhei Kamiya, Masaru Kamiya, Takeshi Miyamoto, Masashi Matsukawa, Isao Kondoh, Takashi Ito, Kazuhiro Takeuchi
  • Patent number: 10400610
    Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end, and a tip shroud extending from the tip end. The tip shroud includes a shroud plate that includes a pressure side edge. The pressure side edge includes a primary contact surface configured to couple against an adjacent tip shroud, and a notch extending at least partially downstream from the primary contact surface.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: September 3, 2019
    Assignee: General Electric Company
    Inventors: William Scott Zemitis, Richard Ryan Pilson, Melbourne James Myers
  • Patent number: 10316675
    Abstract: A seal device of a turbine includes: at least one step surface disposed on a radially outer surface of a rotor blade facing a first radial-directional gap or on an outer peripheral surface of a rotor facing a second radial-directional gap, the at least one step surface facing upstream in a flow direction of a fluid and dividing the radially outer surface of the rotor blade or the outer peripheral surface of the rotor into at least two sections in an axial direction of the rotor; at least two seal fins protruding toward the at least two sections, respectively, from a surrounding member or the stationary vane, and facing the at least two sections via a seal gap, respectively, the at least two seal fins forming a cavity which extends over the at least one step surface in the axial direction of the rotor between each other.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: June 11, 2019
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yoshihiro Kuwamura, Hiroharu Oyama, Yoshinori Tanaka, Hideaki Sugishita
  • Patent number: 10260522
    Abstract: The present disclosure provides a liner system for a turbine engine. The liner system includes a fan track liner panel that is positionable axially within a casing that is arranged around a rotatable fan and that forms a blade containment zone. The fan track liner panel is further positionable radially outward of the rotatable fan. The fan track liner panel includes a body that extends a length of the fan track liner panel from a fore portion of the fan track liner panel to an aft portion of the fan track liner panel. The fan track liner panel is configured to be directly secured to the casing by a fastener that extends through only part of the body and entirely through the casing within the blade containment zone such that the aft portion of the fan track liner panel abuts an interior surface of the casing.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: April 16, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Robert Warren Heeter, Timothy John Unton, Eric Engebretsen, Jonathan Rivers
  • Patent number: 10208616
    Abstract: A turbomachine, particularly an aircraft engine, having a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades, is disclosed, wherein the stator has at least one abradable layer, and wherein each rotating blade has a blade tip that is lowered radially inward, at least in sections, proceeding from a leading edge on the side of the rotating blades in the direction of a trailing edge on the side of the rotating blades, and with a blade tip region that extends downstream from the leading edge runs into the abradable layer during operation of the turbomachine.
    Type: Grant
    Filed: June 26, 2015
    Date of Patent: February 19, 2019
    Assignee: MTU AERO ENGINES AG
    Inventors: Axel Mattschas, Helmut Eibl, Sergio Elorza Gomez, Dirk Henrichs
  • Patent number: 10113439
    Abstract: The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: October 30, 2018
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 10066495
    Abstract: An assembly for a turbine engine includes an inner platform, and outer platform and a plurality of structural inlet guide vanes. The outer platform circumscribes the inner platform. The structural inlet guide vanes are arranged around an axis, and extend radially between and are connected to the inner platform and the outer platform. A first of the structural inlet guide vanes includes a structural vane body that is configured from or otherwise includes an organic matrix composite.
    Type: Grant
    Filed: January 14, 2014
    Date of Patent: September 4, 2018
    Assignee: United Technologies Corporation
    Inventors: Steven Roberts, Kenneth F. Tosi, Isaac J. Hogate, George A. Salisbury
  • Patent number: 9995159
    Abstract: A stator of a low-pressure compressor of an axial-flow turbomachine. The stator includes an annular row of stator blades including radial extremities which pass through the openings of an internal shroud, and which include radial retaining slots having tapers formed by hooks. The stator includes a ring for retaining the blades on the internal shroud. The ring is curved circumferentially in order to be inserted into a plurality of retaining slots and exhibits the form of a strip having an arched transversal profile which is in abutment against the tapers, in such a way as to maintain the ring in the interior of the slots. The shroud includes an annular layer of abradable material made from silicone, which encloses the ring in such a way as to block the curvature of the arched profile of the ring in order to prevent it from disengaging from the tapers of the slots.
    Type: Grant
    Filed: April 24, 2015
    Date of Patent: June 12, 2018
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Damien Verhelst
  • Patent number: 9617863
    Abstract: A gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region. Between the first and second contact regions, this stator vane leading edge has an axial offset of no more than 0.6% of a radial height of the stator vane leading edge.
    Type: Grant
    Filed: July 8, 2014
    Date of Patent: April 11, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Inga Mahle, Norbert Huebner, Rudolf Stanka, Gottfried Schuetz, Norman Cleesattel
  • Patent number: 9587506
    Abstract: A segment of an abradable ring seal for a turbomachine, includes: a reinforcing support; a composite fabric including fibers impregnated with polymerized resin, and a track of abradable material. The composite fabric is interposed between the reinforcing support 71 and the track of abradable material and is bonded to the reinforcing support, on the one side, and to the track of abradable material, on the other side. The segment of an abradable ring seal has a resistance to tearing in a direction perpendicular to the interface between the track of abradable material and the composite fabric, on the one hand, and between the composite fabric and the reinforcing support, on the other hand, greater than 5.106 newtons per square meter. A process for the manufacture of such a segment is also described.
    Type: Grant
    Filed: June 12, 2014
    Date of Patent: March 7, 2017
    Assignee: COMPOSITE INDUSTRIE
    Inventors: Karl-Heinz Konigs, Gerome Sonois, Philippe Martins
  • Patent number: 9512726
    Abstract: Disclosed are mechanisms for an impeller (10, 20, 40) and method of reducing noise levels while driving fluids with impellers. Exemplary implementations include a hub (21, 41) and multiple blades (22) separably attached to or inseparably formed on the hub. The hub may be used to effectively reduce noise levels during operations of the impeller by having a first cylindrical feature (261), a first number of first ribs (27, 47, 706), and a second number of second ribs (281, 48, 708), while maintaining substantially similar mechanical properties or operational characteristics. The hub may further optionally include a second substantially cylindrical feature (704) that is separably attached to or is inseparably formed on the hub to further enhance one or more properties or characteristics of the hub while serving to reduce the noise level of the impeller.
    Type: Grant
    Filed: July 23, 2013
    Date of Patent: December 6, 2016
    Assignee: JOHNSON ELECTRIC S.A.
    Inventors: Guodong Ren, Anbang Chen, Di Wang, Rui Feng Qin
  • Patent number: 9353632
    Abstract: An aerofoil structure for a rotating blade-row in a casing. The aerofoil structure includes a suction side, a pressure side and a tip therebetween. At least a portion of the tip includes a shaped feature provided on a surface of the tip. The shaped feature has a convergent portion orientated to reduce a gap between the tip and the casing in a direction from the pressure side to the suction side of the aerofoil structure.
    Type: Grant
    Filed: October 7, 2011
    Date of Patent: May 31, 2016
    Assignee: ROLLS-ROYCE plc
    Inventors: Li He, Qiang Zhang, Andrew P Wheeler, Nicholas R Atkins
  • Patent number: 9334877
    Abstract: A fan arrangement (1), in particular for cooling an engine system, comprising: an impeller (10) having one or more blades (4) which in operation convey a medium in the direction of an axis of rotation of the impeller (10) from an inlet side (E) to an outlet side (A); a housing shroud (6) having a base part (61) which extends in the direction of the axis of rotation and surrounds the impeller (10) completely or partially, wherein, on an end of the base part (61) oriented towards the outlet side (A) of the impeller (10), there is provided a discharge flow element (63) which extends radially outwards from the end of the base part (61).
    Type: Grant
    Filed: December 6, 2012
    Date of Patent: May 10, 2016
    Assignee: Robert Bosch GmbH
    Inventors: Stephen Nicholls, Sebastian Hansen, Michael Burkart
  • Patent number: 9303516
    Abstract: A movable blade for a turbomachine, the blade including at its distal end a top portion including opposite first and second side edges and upstream and downstream sealing wipers. Each of the first and second side edges has a substantially Z-shaped profile between the upstream and downstream wipers. On a side of the first side edge, the platform includes a first outwardly projecting rim not connected to either of the upstream and downstream wipers. The platform includes a second outwardly projecting rim, the second rim including a downstream portion connected to the downstream wiper and extending along the second edge, and an upstream portion extending the downstream portion as far as the upstream wiper, and set back relative to the second side edge.
    Type: Grant
    Filed: November 21, 2011
    Date of Patent: April 5, 2016
    Assignee: SNECMA
    Inventors: Yannick Collin, Thomas Lardellier, David Mathieu, Denis Trahot, Christophe Remy, Xavier Godfrind
  • Patent number: 9228318
    Abstract: A cooling device includes: a cooling fan; a shroud provided at an outer circumferential side of the cooling fan; an inner circumferential wall provided on the shroud and adjacent to the outer circumference of the cooling fan so as to surround the cooling fan; an outer circumferential wall provided to surround the inner circumferential wall. An air-flow-direction downstream side end of the outer circumferential wall is positioned at a further downstream position in an air flow direction than an air-flow-direction downstream side end of the inner circumferential wall. The cooling fan is rotatable within a space provided on a radially inner side of the inner circumferential wall. The air-flow-direction downstream side end of the outer circumferential wall is provided at a further upstream position in the air flow direction than an air-flow-direction downstream side end of the cooling fan.
    Type: Grant
    Filed: August 29, 2008
    Date of Patent: January 5, 2016
    Assignee: Komatsu Ltd.
    Inventors: Mitsuo Yabe, Hiroki Shinoda, Masahiro Ikeda, Tomoya Watanabe, Atsushi Kawano, Seiichi Fuchita, Yasuhiro Kusuyama, Teruyuki Matsuki
  • Patent number: 9121297
    Abstract: A brush seal for use between a rotating component and a stationary component in a turbomachine is disclosed. The brush seal according to embodiments of this invention include a set of bristles having a fixed end and a free end, wherein the fixed end is attached to the rotating component, and wherein the set of bristles are angled axially with respect to the rotating component.
    Type: Grant
    Filed: March 28, 2011
    Date of Patent: September 1, 2015
    Assignee: General Electric Company
    Inventors: Xiaoqing Zheng, William Edward Adis, Bernard Arthur Couture, Jr., Michael Dennis Mack, Kristan Brice Sears
  • Patent number: 9022722
    Abstract: A frame assembly of a ring-type fan with a pressure-releasing function includes a fan wheel, a pressuring-releasing portion, and a frame body. The fan wheel is received in an accommodating space of the frame body. The fan wheel has a hub and a plurality of blades. The pressure-releasing portion is formed on free ends of the blades and has a stopping wall and a flange extending from one end of the stopping wall. A pressure-releasing channel is formed between the stopping wall and an inner wall of the frame body. With the pressure-releasing portion being formed on the free ends of the blades, the present invention is capable of delaying the deceleration, improving the fan performance, and reducing its noise.
    Type: Grant
    Filed: November 15, 2011
    Date of Patent: May 5, 2015
    Assignee: Asia Vital Components Co., Ltd.
    Inventors: Wen-Hao Liu, Guan-Chen Yin
  • Patent number: 9017018
    Abstract: An annular seal positionable in a gap is disclosed herein. The annular seal includes a plurality of leaves positioned about a center axis. Each leaf extends to a distal end that is elastically deflectable relative to the center axis to accommodate changes in a size of the gap. The annular seal also includes a ring encircling the center axis and at least partially interconnecting the plurality of leaves together for concurrent installation and removal. The annular seal also includes a plurality of tabs projecting from the ring along the center axis. Each of the tabs is directly connected to at least one of the plurality of leaves such that elastic deformation of one of the plurality of leaves induces bending in the corresponding tab before inducing bending in the ring.
    Type: Grant
    Filed: September 24, 2009
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Corporation
    Inventor: Wade Alan Vest
  • Patent number: 9009965
    Abstract: The present application further describes a method for extending the operating life of a tip shrouded turbine blade that includes the steps of: 1) removing an end located cutter tooth from a seal rail of a tip shroud, the end located cutter tooth including a cutter tooth located at the end of one of the suction side and pressure side of the seal rail of the tip shroud; and 2) attaching a center located cutter tooth to the seal rail of the tip shroud, the center located cutter tooth including a cutter tooth that is located in the approximate center of the seal rail of the tip shroud. In such method, the center located cutter tooth may be attached to the seal rail such that the center located cutter tooth is inside the airfoil if it were projected radially outward from the narrowest point below a tip shroud fillet.
    Type: Grant
    Filed: May 24, 2007
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventors: Daniel Tragesser, Ian Reeves, Christopher Thompson, Todd Moran
  • Publication number: 20150098809
    Abstract: A turbomachine is described, which includes an annular space seal for at least reducing a fluid exchange between an annular space, through which a main stream flows, and at least one cavity situated radially on the inside and/or radially on the outside of the annular space, the annular space seal having a plurality of sheet-like elastic elements, which are oriented in the radial direction of the turbomachine and in the flow direction of a main stream flowing through the particular guide blade row, and thereby acting as a protective device for the rotor and/or stator during a relative axial displacement with respect to the stator in addition to providing an improved cavity coverage.
    Type: Application
    Filed: October 7, 2014
    Publication date: April 9, 2015
    Inventor: Guenter Ramm
  • Patent number: 8967972
    Abstract: A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.
    Type: Grant
    Filed: November 2, 2012
    Date of Patent: March 3, 2015
    Assignee: ALSTOM Technology Ltd.
    Inventors: Herbert Brandl, Igor Tsypkakyin, Philipp Indlekofer
  • Fan
    Patent number: 8961109
    Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.
    Type: Grant
    Filed: October 6, 2008
    Date of Patent: February 24, 2015
    Assignee: Bronswerk Heat Transfer B.V.
    Inventor: Augustinus Wilhelmus Maria Bertels
  • Patent number: 8961117
    Abstract: A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: February 24, 2015
    Assignee: Snecma
    Inventors: Fabrice Marcel Noel Garin, Alain Dominique Gendraud, Gilles Jeannin, Sebastien Jean Laurent Prestel
  • Patent number: 8944757
    Abstract: A fluid machine of an embodiment includes a sealing portion formed of an annular minute gap between a runner band of a runner configuring a rotating portion and a sealing liner which is a stationary portion and arranged in opposition to the runner band. A groove having a quadrangular cross-sectional shape is formed circumferentially on a surface of the sealing liner configuring the sealing portion. In a cross section perpendicular to a groove forming direction of the groove, an angle ?, formed between a side WU of the groove on the most upstream side with respect to the flowing direction of the leakage flow and a side W0 of the groove which is on an extended line of the surface of the sealing liner, is determined to be 15° or more and 40° or less.
    Type: Grant
    Filed: September 9, 2011
    Date of Patent: February 3, 2015
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Hideyuki Kawajiri, Naritoshi Nakagawa
  • Patent number: 8939706
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of ridges in planform patterns, establishing upper and lower wear zones. The lower wear zone reduces, redirects and/or blocks blade tip downstream airflow leakage, while the upper wear zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone. An elongated first ridge in the lower wear zone terminates in a continuous surface plateau. A plurality of second ridges or nibs, separated by grooves, project from the plateau, forming the upper wear zone. Each of the second ridges has a planform cross section smaller than the plateau planform cross section and a height smaller than the first ridge height. Some embodiments of the second ridges have spacing, planform cross sections, heights and separating groove dimensions selected for shearing when contacted by turbine blade tips.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Neil Hitchman, David G. Sansom, Barrry L. Allmon, Jonathan E. Shipper, Jr., Cora Schillig, Gary B. Merrill, Dimitrios Zois, Ramesh Subramanian
  • Patent number: 8939707
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of stepped first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Each stepped first ridge has a first portion proximal the substrate surface with a pair of first opposed lateral walls terminating in a plateau, and a second portion terminating in a ridge tip. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, which at and below first portion height, optimizes engine airflow characteristics, while the upper zone, between the plateau and the second portion ridge is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Gm Salam Azad, Zhihong Gao, Neil Hitchman, David G. Sansom, Barrry L. Allmon
  • Patent number: 8939716
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with nested loop pattern abradable surface ridges and grooves. The nested loops comprise nested fully closed loops or a spiraling maze pattern loop. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Kok-Mun Tham, Vincent P. Laurello, Gm Salam Azad, Nicholas F. Martin, Jr.
  • Patent number: 8939705
    Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting rows of first ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. The abradable component embodiments have a multi-depth grooves formed in the abradable substrate surface between pairs of elongated continuous tip surface first ridges. These ridge and multi-depth groove embodiments have first lower and second upper wear zones. The lower zone, in the deeper grooves, optimizes engine airflow characteristics, while the upper zone, in the shallower grooves, is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: January 27, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Ching-Pang Lee, Kok-Mun Tham
  • Patent number: 8939715
    Abstract: A turbine bucket tip clearance control system includes a rotor assembly having a rotor supporting a plurality of axially spaced wheels, each wheel mounting an annular row of buckets, the annular row of buckets on at least one of the plurality of axially-spaced wheels having a radially outer tip shroud provided with at least one seal tooth. A stator assembly includes a radially inwardly facing, axially-stepped surface, formed with radially inner and outer seal surfaces connected by a shoulder. The stator assembly and rotor assembly are moveable axially relative to each other, enabling selective positioning of the at least one seal tooth radially opposite one of the radially inner and outer seal surfaces to thereby selectively alter a clearance gap between the at least one seal tooth and the radially inward facing axially-stepped surface.
    Type: Grant
    Filed: March 22, 2010
    Date of Patent: January 27, 2015
    Assignee: General Electric Company
    Inventor: Harold Edward Miller
  • Patent number: 8936431
    Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.
    Type: Grant
    Filed: June 8, 2012
    Date of Patent: January 20, 2015
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Sumeet Soni
  • Patent number: 8926271
    Abstract: The present invention relates to a pressure seal (7) of a turbomachine stator, said seal (7) comprising a first abradable surface opposite a rotor portion of the turbomachine and a second surface in contact with an inner shroud (3) of the stator, said seal (7) comprising a plurality of component units (10), each component unit (10) having, on its first abradable surface, a circumferential step (9) creating an obstacle in the circumferential direction of the inner shroud (3).
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: January 6, 2015
    Assignee: Techspace Aero S.A.
    Inventor: Stéphane Hiernaux
  • Patent number: 8920126
    Abstract: An object is to provide a turbine and a turbine rotor blade in which it is possible to ensure the strength of the turbine rotor blade and to improve the performance thereof. The turbine includes: rotor blades that rotate about a rotational axis in a main flow channel of a casing; stator vanes that are disposed in the casing; a tip shroud that is disposed at a radially-outward end of each of the rotor blades and whose length in the direction along the rotational axis is reduced as the distance from the rotor blade increases; and a cavity portion that is formed at a position in the casing facing the rotor blades and in which the tip shroud is accommodated. An inclination angle of the inner periphery of the tip shroud is larger than an average inclination angle that is an inclination angle of the inner periphery of the casing, averaged from the trailing edge of the stator vanes disposed at the upstream side of a main flow to the cavity portion disposed at the downstream side of the main flow.
    Type: Grant
    Filed: December 7, 2009
    Date of Patent: December 30, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Koichiro Iida
  • Publication number: 20140294572
    Abstract: A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment has two or more spaced passageways. In use, a respective support bar can be contained within each passageway. The support bars allow attachment of the seal segment to the engine casing. Each passageway has an elliptical or substantially elliptical cross-section with a minor diameter and a major diameter, the minor diameter being substantially aligned with the radial direction. The respective support bar has a correspondingly elliptical or substantially elliptical cross-section for a close fit in the passageway.
    Type: Application
    Filed: March 25, 2014
    Publication date: October 2, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Steven HILLIER, Alex WONG
  • Publication number: 20140261582
    Abstract: An appliance pump is provided having a seal ring that can reduce or eliminate noise that can occur when e.g., the pump experiences air or an under-primed condition. The seal ring uses one or biasing members to urge the seal ring into a position to prevent rattling or other vibrations that cause such noise. The present invention also includes seal ring having such construction.
    Type: Application
    Filed: March 14, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Steven Chadwick Koepke
  • Patent number: 8834096
    Abstract: In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45) with a plurality of outer teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow. The teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).
    Type: Grant
    Filed: November 29, 2011
    Date of Patent: September 16, 2014
    Assignee: Alstom Technology Ltd.
    Inventor: Alexander Anatolievich Khanin
  • Patent number: 8807928
    Abstract: The present application provides a tip shroud assembly for use with a turbine engine. The tip shroud assembly may include a shroud, a seal rail positioned on the shroud, and a contoured fillet attaching the seal rail to the shroud.
    Type: Grant
    Filed: October 4, 2011
    Date of Patent: August 19, 2014
    Assignee: General Electric Company
    Inventors: Spencer Aaron Kareff, Jason Herzlinger, Harish Bommanakatte
  • Publication number: 20140212261
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.
    Type: Application
    Filed: December 19, 2012
    Publication date: July 31, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: UNITED TECHNOLOGIES CORPORATION
  • Patent number: 8753093
    Abstract: A turbine bucket includes an airfoil portion and a tip shroud at a radially outer end of the airfoil portion. The tip shroud includes a first radially inner tip shroud component formed integrally with the airfoil portion and composed of a first metal material, and a second radially outer structural tip shroud component composed of a second metal material bonded to the first radially inner tip shroud component.
    Type: Grant
    Filed: October 19, 2010
    Date of Patent: June 17, 2014
    Assignee: General Electric Company
    Inventor: Gary Liotta
  • Patent number: 8740572
    Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.
    Type: Grant
    Filed: November 1, 2010
    Date of Patent: June 3, 2014
    Assignee: Alstom Technology Ltd.
    Inventors: Matthias Hoebel, Günter Ambrosy, Felix Reinert, Stephane Barril
  • Patent number: 8727713
    Abstract: A rotor oscillation preventing structure for a steam turbine includes: a stator vane 3; a moving blade 1; a shroud cover 2 installed on an outer circumferential side distal end of the moving blade 1; and a plurality of seal fins 6 installed, at any interval in the axial direction of a rotor, on an wall surface of a stationary body located on an outer circumferential side of the shroud cover 2, a whirl preventing structure comprised of whirl preventing plates 9 or whirl preventing grooves 11 is provided at a shroud cover inlet return portion 10 of the shroud cover 2 so as to block the whirl flow of leakage flow 8 on an upstream side in an operating steam flow direction of the seal fins to reduce an absolute velocity component of the leakage flow 8 in a rotational direction of the rotor.
    Type: Grant
    Filed: February 15, 2011
    Date of Patent: May 20, 2014
    Assignee: Hitachi, Ltd.
    Inventors: Hideki Ono, Takeshi Kudo, Kenichi Murata, Masataka Sonobe, Tsutomu Sugiyama
  • Patent number: 8708639
    Abstract: The present application provides an axial flow turbine. The axial flow turbine may include a stator casing and a turbine bucket positioned about the stator casing. A tip shroud may be positioned on the turbine bucket. A shroud tail may be attached to the tip shroud at a downstream end of the tip shroud.
    Type: Grant
    Filed: October 11, 2010
    Date of Patent: April 29, 2014
    Assignee: The Coca-Cola Company
    Inventor: Moorthi Subramaniyan
  • Patent number: 8662835
    Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.
    Type: Grant
    Filed: March 13, 2009
    Date of Patent: March 4, 2014
    Assignee: SNECMA
    Inventors: Thierry Fachat, Patrick Joseph Marie Girard, Jean-Luc Soupizon
  • Publication number: 20140023490
    Abstract: A fastener is provided for connecting two or more structural elements having matching apertures which, when aligned, form a frusto-conical cavity. The fastener includes a body portion having a frusto-conical outer surface which is receivable in the aligned apertures of the structural elements such that the outer surface of the body portion is in mating engagement with the cavity formed by the aligned apertures. The fastener further includes an elongate member which extends from the body portion at the narrow end of the frusto-conical outer surface. The fastener further includes a fixing element carried by the elongate member. The fixing element is operable to exert a clamping force between the frusto-conical outer surface and the fixing element to retain the structural elements in connection therebetween. The fastener further includes a through-hole which extends along the elongate member and which allows fluid communication between opposing sides of the connected structural elements.
    Type: Application
    Filed: July 18, 2013
    Publication date: January 23, 2014
    Inventor: Steven HILLIER
  • Patent number: 8632309
    Abstract: A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: January 21, 2014
    Assignee: Alstom Technology Ltd
    Inventors: Igor Tsypkaykin, Ruben Valiente, Brian Kenneth Wardle, Beat Von Arx, Andre Saxer
  • Publication number: 20140003918
    Abstract: A seal structure for a gas turbine engine, the seal structure including first and second components located adjacent to each other and forming a barrier between high and low pressure zones. A seal cavity is defined in the first and second components, the seal cavity extending to either side of an elongated gap extending generally in a first direction between the first and second components. A seal member is positioned within the seal cavity and spans across the elongated gap. The seal member includes first and second side edges extending into each of the components in a second direction transverse to the first direction, and opposing longitudinal edges extending between the side edges generally parallel to the first direction. The side edges include a groove formed therein for effecting a reduction of gas flow around the seal member at the side edges.
    Type: Application
    Filed: June 2, 2010
    Publication date: January 2, 2014
    Inventors: Santiago Salazar, Andrew Gisch
  • 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: 8585357
    Abstract: A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: November 19, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Franco DiPaola, Roger Gates