Segmental Shroud Patents (Class 416/191)
  • Patent number: 11371363
    Abstract: A tip shroud may include a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading and/or trailing Z-notch of the tip shroud, and/or upstream and/or downstream radially outer surfaces of a wing. The surface profiles may have a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and perhaps thickness, set forth in a respective table.
    Type: Grant
    Filed: June 4, 2021
    Date of Patent: June 28, 2022
    Assignee: General Electric Company
    Inventors: Michael James Gutta, William Scott Zemitis
  • Patent number: 11274561
    Abstract: A vane assembly includes a plurality of vane units and a connecting part. Each vane unit includes a base having a through-hole positioned between opposing longitudinal faces of the base. The connecting part includes a lacing bar that is insertable into and through the through-holes for coupling at least two adjacent vane units into the vane assembly. In the vane assembly the connecting part is arranged through the through holes of the plurality of vane units clamping the vane units on the lacing bar.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: March 15, 2022
    Assignee: SULZER MANAGEMENT AG
    Inventors: Jozef H. G. Mattheij, Twan Antonius Martinus Althuizen
  • Patent number: 11248620
    Abstract: An electric blower (10) is disclosed as including a brushless motor (16), and an axial fan (18, 18C) driven by the motor, the motor being operable at a first speed of rotation of 15,000 revolutions per minute (rpm) and a second speed of rotation of 18,000 rpm, the axial fan including a hub (34C) and a plurality of fan blades (36C) engaged with the hub, the hub having a hub diameter (?H), the axial fan having an outer diameter (?T), and ? H ? T being between substantially 0.6 and substantially 0.65.
    Type: Grant
    Filed: September 18, 2019
    Date of Patent: February 15, 2022
    Assignee: Techtronic Cordless GP
    Inventor: Koon For Chung
  • Patent number: 11242762
    Abstract: An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.
    Type: Grant
    Filed: November 21, 2019
    Date of Patent: February 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Alyson T. Burdette, Bryan P. Dube, Rutva A. Patel, Nicholas Broulidakis
  • Patent number: 11078797
    Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.
    Type: Grant
    Filed: November 14, 2019
    Date of Patent: August 3, 2021
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Shashwat Swami Jaiswal, Gunnar Leif Siden, Zachary James Taylor
  • Patent number: 11073032
    Abstract: A cascade array vane is provided that includes a vane, a first longitudinal portion, a second longitudinal portion, and at least one coupling feature. The vane includes an airfoil portion extending between a first end and a second end. The first longitudinal portion is disposed at the first end of the vane extending outwardly from the vane. The second longitudinal portion is disposed at the second end of the vane extending outwardly from the vane. The at least one coupling feature is incorporated with at least one of the first longitudinal portion or the second longitudinal portion.
    Type: Grant
    Filed: July 25, 2018
    Date of Patent: July 27, 2021
    Assignee: Rohr, Inc.
    Inventor: Teresa Kruckenberg
  • Patent number: 10968747
    Abstract: In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Eric D. Gray, Razvan Virgil Florea, Mark B. Stucky, Ray-Sing Lin
  • Patent number: 10947980
    Abstract: Embodiments of the invention are directed to a rotor for use in molten metal and devices including the rotor. The rotor has a rotor body and blades, wherein each blade includes a tip that is at least twice as hard as the rotor body.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: March 16, 2021
    Assignee: Molten Metal Equipment Innovations, LLC
    Inventor: Paul V. Cooper
  • Patent number: 10934863
    Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Morrison, Ted J. Freeman
  • Patent number: 10895159
    Abstract: An assembly includes: a movable blade for a turbomachine including a tip; and a removable part including an anti-wear material, configured to be attached removably to an edge of the tip to limit wear of the tip.
    Type: Grant
    Filed: May 24, 2018
    Date of Patent: January 19, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Vijeay Patel, Pragash Douglas, Quentin Bruno Guy Andre Emile Lievoux, Pauline Namvong
  • Patent number: 10858947
    Abstract: A method for measuring a pre-twist amount of a blade includes a spreading dimension acquiring step, a misalignment acquiring step, a correcting step, and a pre-twist amount acquiring step. In the spreading dimension acquiring step, circumferential spreading dimensions of each shroud of two rotor blades are acquired. In the misalignment acquiring step, a misalignment amount in the direction of the axis between the shrouds of two rotor blades adjacent to each other in the circumferential direction is measured. In the correcting step, the spreading dimension acquired in the spreading dimension acquiring step is corrected on the basis of the misalignment amount acquired by the misalignment acquiring step. In the pre-twist amount acquiring step, the pre-twist amount of the blade is acquired on the basis of the spreading dimension corrected in the correcting step.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: December 8, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Yuzo Tsurusaki, Yuki Nakamura, Yuichi Sasaki
  • Patent number: 10781700
    Abstract: In a turbine rotor blade assembly 1 of the present invention, each turbine rotor blade 10 includes a platform 11 having a blade root 12 fixed to a turbine disk 30, a profile 13 rising from the platform 11, and a shroud 14 provided at a top end of the profile 13. The shroud 14 of the present invention includes a first contact end part 15 that comes into contact with an adjacent shroud adjacent to one end side in a circumferential direction, a second contact end part 16 that comes into contact with an another adjacent shroud adjacent to the other end side in the circumferential direction, and a main body part disposed between the first and second contact end parts 15 and 16. One or both of the first and second contact end parts 15 and 16 are lower in rigidity than the main body part.
    Type: Grant
    Filed: March 6, 2017
    Date of Patent: September 22, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION
    Inventors: Nobuyori Yagi, Naoyuki Nagai, Shin Yanagisawa, Yuki Nakamura
  • Patent number: 10767498
    Abstract: A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.
    Type: Grant
    Filed: April 3, 2018
    Date of Patent: September 8, 2020
    Assignee: Rolls-Royce High Temperature Composites Inc.
    Inventor: Stephen Harris
  • Patent number: 10738634
    Abstract: The present disclosure provides an airfoil assembly comprising a first segment comprising a first shroud and a second shroud radially outward of the first shroud, a second segment comprising a first shroud and a second shroud radially outward of the first shroud, and a first coupling coupled to at least one of the first shroud or the second shroud of the first segment and a second coupling coupled to at least one of the first shroud or the second shroud of the second segment, wherein the first segment and the second segment are coupled together by a first land of the first coupling and a second land of the second coupling.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Scott H. Lamson
  • Patent number: 10731481
    Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.
    Type: Grant
    Filed: November 1, 2016
    Date of Patent: August 4, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Ted J. Freeman, James Glen Schwefel, Phil Bastnagel
  • Patent number: 10669861
    Abstract: An airfoil may comprise an airfoil body having a leading edge, a trailing edge, an inner diameter end wall and an outer diameter end wall. A first cooling structure may be disposed within the airfoil body. The first cooling structure may comprise a first rib extending between the inner diameter end wall and the outer diameter end wall and may define a first radial passage configured to conduct a cooling airflow in a radial direction through the airfoil body. A second cooling structure may be disposed within the airfoil body. The second cooling structure may comprise a first baffle defining an axial passage configured to conduct the cooling airflow in an axial direction toward the trailing edge of the airfoil body.
    Type: Grant
    Filed: February 15, 2017
    Date of Patent: June 2, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brandon Spangler, Dominic Mongillo
  • Patent number: 10669864
    Abstract: An unshrouded turbomachine impeller is disclosed. The impeller comprises a hub and a plurality of sequentially arranged blades. Each blade extends from a blade root at the hub to a blade tip and is comprised of a first blade edge and a second blade edge. A flow vane is formed between each pair of neighboring blades. A connection member extends across each flow vane between neighboring blades and rigidly or monolithically connects a first modal displacement region of a first one of the pair of neighboring blades to a second modal displacement region of a second one of the pair of neighboring blades.
    Type: Grant
    Filed: July 18, 2016
    Date of Patent: June 2, 2020
    Assignee: NUOVO PIGNONE SRL
    Inventors: Giuseppe Iurisci, Angelo Grimaldi, Simone Corbo
  • Patent number: 10648346
    Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.
    Type: Grant
    Filed: July 6, 2016
    Date of Patent: May 12, 2020
    Assignee: General Electric Company
    Inventors: Xiuzhang James Zhang, Kevin Richard Kirtley, Lisa DeBellis
  • Patent number: 10641288
    Abstract: Described is a method for operating a compressor of a turbomachine, in which, when considered in the direction of a main flow, an, in particular, radially averaged degree of reaction has dropped in a front compressor area from a maximum to a minimum, is held constant or virtually constant across a central compressor area up into a rear compressor area, an, in particular, radially averaged degree of reaction being adjusted in the rear compressors area which is closer to the minimum than to the maximum, and a residual swirl of at least 47┬░ is present in the middle section, and a compressor and a turbomachine.
    Type: Grant
    Filed: November 22, 2016
    Date of Patent: May 5, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Tim Schneider, Sergio Elorza Gomez
  • Patent number: 10619484
    Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the cooling of at least portions of a turbine bucket. In one embodiment, the invention provides a method of cooling at least a portion of a turbine bucket, the method comprising: during operation of a turbine, altering a swirl velocity of purge air beneath a platform lip extending axially from the platform, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of voids disposed along a length of an angel wing extending axially from a face of a shank portion of the turbine bucket.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: April 14, 2020
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Soumyik Kumar Bhaumik, Clint Luigie Ingram
  • Patent number: 10590777
    Abstract: The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a first cooling channel and a second cooling channel. The first cooling channel is radially spaced apart from the second cooling channel. Coolant flows in a first direction through the first cooling channel and in a second direction through the second cooling channel. The first direction is different than the second direction.
    Type: Grant
    Filed: June 30, 2017
    Date of Patent: March 17, 2020
    Assignee: General Electric Company
    Inventor: Robert Alan Brittingham
  • Patent number: 10544687
    Abstract: The present invention relates to an improved cast-to-size gas turbine blade comprising a blade tip shroud with a stiffening rib extending outwardly from the section of the outer side of the shroud platform located between the upstream sealing fin and the upstream edge. The stiffening rib having substantially planar top surface in form of a trapezium, and two sloping sidewalls extending between the upstream sealing fin and the upstream edge on each side of the top surface and connecting said top surface with adjacent surface of the outer side of the shroud platform. The form of the stiffening rib allows to obtain an improved shroud configuration of reduced overall blade mass, capable of providing sufficient stiffening of the shroud, reducing vibrations of the shroud platform, creep curling of the shroud edges and bending stress at the intersection of the airfoil and of the shroud.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: January 28, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
  • Patent number: 10508554
    Abstract: A turbine bucket according to embodiments includes: a base; a blade coupled to base and extending radially outward from base, blade including: a body having: a pressure side; a suction side opposing pressure side; a leading edge between pressure side and suction side; and a trailing edge between pressure side and suction side on a side opposing leading edge; and a plurality of radially extending cooling passageways within body; and a shroud coupled to blade radially outboard of blade, shroud including: a plurality of radially extending outlet passageways fluidly connected with a first set of the plurality of radially extending cooling passageways within body; and an outlet path extending at least partially circumferentially through shroud and fluidly connected with all of a second, distinct set of the plurality of radially extending cooling passageways within body.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: December 17, 2019
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Shashwat Swami Jaiswal, Gunnar Leif Siden, Zachary James Taylor
  • Patent number: 10502069
    Abstract: A rotor blade includes an airfoil defining at least one cooling passage and a camber line extending from a leading edge to a trailing edge. The rotor blade further includes a tip shroud coupled to the airfoil, the tip shroud and the airfoil defining a core fluidly coupled to the at least one cooling passage, the core including a plurality of outlet apertures, each of the plurality of outlet apertures including an opening defined in an exterior surface of the tip shroud. A first outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is between 15 degrees from parallel to and parallel to the camber line at the trailing edge. A second outlet aperture is oriented to exhaust cooling fluid through the opening thereof in a direction that is greater than 15 degrees from parallel to the camber line at the trailing edge.
    Type: Grant
    Filed: June 7, 2017
    Date of Patent: December 10, 2019
    Assignee: General Electric Company
    Inventors: Mark Andrew Jones, Bradley Taylor Boyer
  • Patent number: 10502073
    Abstract: A rotor assembly is provided. The rotor assembly includes a plurality of blades spaced circumferentially. An airfoil of each blade includes a pressure side, a suction side, a pressure side nub extending from the pressure side, and a suction side nub extending from the suction side. An airfoil length is greater than one of (i) 40 inches, wherein the rotor is configured for operation at about 3600 rpm, and (ii) 48 inches, wherein the rotor is configured for operation at about 3000 rpm. The rotor assembly also includes a plurality of sleeves. Each of the sleeves extends from a first end to a second end. The first end is coupled to the pressure side nub of a first of the blades and the second end is coupled to the suction side nub of an adjacent second of the blades.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: December 10, 2019
    Assignee: General Electric Company
    Inventors: Robert Edward Deallenbach, John James Ligos, Kristopher John Frutschy
  • Patent number: 10486255
    Abstract: A method for low heat welding includes providing short circuit pulse Metal Inert Gas (MIG) welding at less than a rate of about a twenty (20) inch a minute travel speed.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventor: William M. Rose
  • Patent number: 10472974
    Abstract: In one aspect, the present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining at least one cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a core fluidly coupled to the cooling passage. A maximum radial depth of the core is at least six times greater than a minimum hydraulic diameter of a largest cooling passage of the at least one cooling passage.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: November 12, 2019
    Assignee: General Electric Company
    Inventors: Mark Andrew Jones, James Tyson Balkcum, III
  • Patent number: 10443392
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: October 15, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier Delabriere, Laurent Patrick Coudert, Jean-Armand Marc Destouches, Daniel Marius Man
  • Patent number: 10443393
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: October 15, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pascal Pierre Routier, Vincent Nicolas Leonardon, Daniel Marius Man, Guillaume Jochen Scholl
  • Patent number: 10408063
    Abstract: A turbine blade having a labyrinth of internal channels for circulation of coolant received through an inlet formed in a terminal portion of a blade root. A labyrinth geometry includes: (i) the inlet arranged on an axially upstream face of the terminal portion leading to an upstream duct portion having a first section adjacent the inlet and a second section having a reduced cross-section compared to the first section, (ii) a leading edge passage intersecting with the first section and extending through a blade body towards a tip of the blade, where a proximal end of the leading edge passage is angled towards a direction of incoming air flow, (iii) a main blade passage intersecting with a downstream duct portion arranged in axial alignment with, and separate from, the upstream duct portion, and (iv) a restrictor passage intersecting with a mid-blade passage and extending towards a mid-blade duct portion.
    Type: Grant
    Filed: March 30, 2016
    Date of Patent: September 10, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Stephen Christopher Diamond
  • Patent number: 10385702
    Abstract: A turbomachinery rotor blade is provided having an aerofoil body, and a hole penetrating the aerofoil body from a suction surface to a pressure surface thereof. The hole is suitable to receive a lacing wire. The blade further has a protrusion from the suction or pressure surface. The protrusion extends in a downstream direction from a downstream side of the hole and/or extends in an upstream direction from an upstream side of the hole, thereby disturbing the suction or pressure surface to locally thicken the aerofoil body adjacent the hole. The maximum radial extent of the protrusion in the radially outward direction of the blade is radially coterminous with the outboard side of the hole, and the maximum radial extent of the protrusion in the radially inward direction of the blade is radially coterminous with the inboard side of the hole.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: August 20, 2019
    Assignee: NAPIER TURBOCHARGERS LTD
    Inventor: Neil Ryan Thomas
  • Patent number: 10364703
    Abstract: The invention relates to the field of turbomachines, and more specifically to an annular element (13) for a turbomachine casing, which has at least one inside face (14) defining a flow passage for a working fluid of the turbomachine, an outside face (15), and a damper (18), comprising at least one resilient coil turn (18a, 18b, 18c) fitted tightly around a surface of revolution (15a) of the outside face (15), in such a manner as to exert pressure on said surface of revolution (15a). The present invention also relates to damping a rotating wave of distortion of such an annular element (13) for a turbomachine casing, wherein said rotating wave is damped by friction between said surface of revolution (15a) and the at least one coil turn (18a, 18b, 18c) of the damper (18).
    Type: Grant
    Filed: November 4, 2014
    Date of Patent: July 30, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: S├ębastien Lionel Guingo, Joris Brousselle
  • Patent number: 10344599
    Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes an airfoil, a tip shroud having a side surface and a radially outer surface, and a transition portion coupling the tip shroud to the airfoil. The airfoil, the transition portion, and the tip shroud collectively define a primary cooling passage therein. The primary cooling passage includes a primary cooling passage outlet defined by the side surface of the tip shroud.
    Type: Grant
    Filed: May 24, 2016
    Date of Patent: July 9, 2019
    Assignee: General Electric Company
    Inventor: Fred Thomas Willett, Jr.
  • Patent number: 10287901
    Abstract: A first stage vane array of a high pressure turbine that may be for a geared turbofan engine includes a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis. Each airfoil has a leading edge and a trailing edge with the trailing edge being circumferentially separated by the next adjacent trailing edge by a pitch distance. The leading a trailing edges of each one of the plurality of airfoils are axially separated by an axial chord length. A pitch-to-chord ratio of the pitch distance over the axial chord length is equal to or greater than 1.7.
    Type: Grant
    Filed: November 11, 2015
    Date of Patent: May 14, 2019
    Assignee: United Technologies Corporation
    Inventor: Andrew S. Aggarwala
  • Patent number: 10253643
    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path.
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Daniel Patrick Kerns, Brandon ALlanson Reynolds
  • Patent number: 10253638
    Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.
    Type: Grant
    Filed: August 12, 2015
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
  • Patent number: 10247007
    Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: May 2, 2017
    Date of Patent: April 2, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Neil Ristau, Mehmet Suleyman Ciray, Jason Douglas Herzlinger
  • Patent number: 10202852
    Abstract: A rotor blade includes an airfoil portion that extends in a radial direction from a root end to a tip end. A plurality of internal airfoil cooling passages is defined in the airfoil portion. The rotor blade also includes a tip shroud. The tip shroud includes a shroud plate coupled to the tip end. A plurality of tip shroud cooling passages is defined within the shroud plate. Each of the tip shroud cooling passages extends within the shroud plate in a direction generally transverse to the radial direction. Each tip shroud passage includes an inlet coupled in flow communication with at least one of the airfoil cooling passages, and an exit opening defined in, and extending therethrough, a radially outer surface of the tip shroud. The exit opening is coupled in flow communication with the inlet.
    Type: Grant
    Filed: November 16, 2015
    Date of Patent: February 12, 2019
    Assignee: General Electric Company
    Inventors: Shashwat Swami Jaiswal, Rohit Chouhan
  • Patent number: 10138736
    Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: November 27, 2018
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Spencer Aaron Kareff
  • Patent number: 10018066
    Abstract: What is described is a partial platform. The partial platform includes a leading edge, a trailing edge, a first circumferential edge and a second circumferential edge. The first circumferential edge and the second circumferential edge are both swept such that a central circumferential axis forms a substantially rounded or squared S shape.
    Type: Grant
    Filed: September 23, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Philip Robert Rioux
  • Patent number: 9957818
    Abstract: A removably attachable snubber assembly for turbine blades includes a turbine blade airfoil including a trailing edge and a leading edge joined by a pressure side and a suction side to provide an outer surface extending in a radial direction to a tip. At least one snubber attachment platform is integrally formed onto the outer surface of the turbine blade airfoil. The at least one snubber attachment platform includes an interlocking mechanism. A snubber is removably attachable to the at least one snubber attachment platform, the snubber including a first end, a second end, a trailing edge, a leading edge, a snubber length, and a snubber width. The snubber also includes a removable attachment mechanism on at least one of the first end and the second end that connects with the interlocking mechanism on the at least one snubber attachment platform.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: May 1, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Nicholas F. Martin, Jr., David J. Wiebe
  • Patent number: 9915272
    Abstract: A turbomachine blade of the type having a metal lower coupling root, a metal upper coupling head, and a metal airfoil-shaped oblong member designed to connect the coupling root rigidly to the coupling head; the airfoil-shaped oblong member having a substantially airfoil-shaped main plate-like element connected to the coupling root and to the coupling head, and which is divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from and formed in one piece with the coupling head; and a center plate-like body, which is located between the lower and upper connecting fins, is shaped/designed to form an extension of the lower and upper connecting fins, and is butt-welded to, to form one piece with, the lower and upper connecting fins.
    Type: Grant
    Filed: August 15, 2016
    Date of Patent: March 13, 2018
    Assignee: PIETRO ROSA T.B.M. S.R.L.
    Inventor: Andrea Maurizio
  • Patent number: 9879549
    Abstract: An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.
    Type: Grant
    Filed: May 3, 2012
    Date of Patent: January 30, 2018
    Assignee: SNECMA
    Inventor: Laurent Gilles Dezouche
  • Patent number: 9816382
    Abstract: A turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: November 14, 2017
    Assignee: Pietro Rosa T.B.M. S.r.l.
    Inventor: Andrea Maurizio
  • Patent number: 9816380
    Abstract: Low-pressure turbine rotors for a thermoelectric power station include an interconnection of slender blades. The rotor includes blades bearing caps being roughly in the shape of a chevron.
    Type: Grant
    Filed: March 6, 2014
    Date of Patent: November 14, 2017
    Assignee: General Electric Technology GmbH
    Inventors: Michel Floch, Arnaud Buguin, Julien Lemaire
  • Patent number: 9790802
    Abstract: A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element.
    Type: Grant
    Filed: May 11, 2012
    Date of Patent: October 17, 2017
    Assignees: SNECMA, HERAKLES
    Inventors: Ivan Herraiz, Clement Roussille, Julien Mateo, Alain Allaria, Jean-Luc Soupizon
  • Patent number: 9759073
    Abstract: A turbine airfoil is provided with at least one insert positioned in a cavity in an airfoil interior. The insert extends along a span-wise extent of the turbine airfoil and includes first and second opposite faces. A first near-wall cooling channel is defined between the first face and a pressure sidewall of an airfoil outer wall. A second near-wall cooling channel is defined between the second face and a suction sidewall of the airfoil outer wall. The insert is configured to occupy an inactive volume in the airfoil interior so as to displace a coolant flow in the cavity toward the first and second near-wall cooling channels. A locating feature engages the insert with the outer wall for supporting the insert in position. The locating feature is configured to control flow of the coolant through the first or second near-wall cooling channel.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: September 12, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Nicholas F. Martin, Jr., David J. Wiebe
  • Patent number: 9759070
    Abstract: The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.
    Type: Grant
    Filed: August 28, 2013
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventors: Xiuzhang James Zhang, Melbourne James Myers, Robert Joseph Testa, Jr., Haiping Wang
  • Patent number: 9689268
    Abstract: A rotor wheel assembly has a rotor wheel including a plurality of dovetail slots. The rotor wheel assembly includes a bucket closure assembly having a leading auxiliary bucket with a dovetail coupled to a dovetail slot and an integral cover having a back side edge oriented at a first angle relative to the rotor wheel rotation axis. The bucket closure assembly includes a closure bucket having a dovetail coupled to a dovetail slot and an integral cover having a front side and a back side edge, where the back side edge is oriented to a second angle and the front side edge is parallel to the back side edge of the leading auxiliary bucket. The bucket closure assembly includes a trailing auxiliary bucket having a dovetail coupled to a dovetail slot and an integral cover having a front side edge parallel to the back side edge of the closure bucket.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: June 27, 2017
    Assignee: General Electric Company
    Inventors: Robert Edward Deallenbach, Ravichandran Pazhur Nair, Douglas Arthur Lupe
  • Patent number: 9683446
    Abstract: A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud. In one non-limiting form the stiffener can have a central ridge that is oriented in an axial direction. Seal members can be included in the shroud that can be used to interact with corresponding seal members in static gas turbine engine structure to discourage a flow of fluid. In one form the shroud includes an upturned leading edge portion.
    Type: Grant
    Filed: December 31, 2013
    Date of Patent: June 20, 2017
    Assignee: Rolls-Royce Energy Systems, Inc.
    Inventor: Don L. Shaffer