Segmental Shroud Patents (Class 416/191)
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Patent number: 11702944Abstract: A high-temperature component including a plurality of cooling passages through which the cooling medium can flow, a header connected to respective downstream ends of the plurality of cooling passages, and one or more outlet passages for discharging the cooling medium flowing into the header to outside of the header. The one or more outlet passages are less in number than the plurality of cooling passages. Respective minimum flow passage cross-sectional areas of the one or more outlet passages are not less than respective flow passage cross-sectional areas of the plurality of cooling passages in a connection between the header and the cooling passages. A sum of the respective minimum flow passage cross-sectional areas of the one or more outlet passages is less than a sum of the respective flow passage cross-sectional areas of the plurality of cooling passages in the connection between the header and the cooling passages.Type: GrantFiled: February 19, 2020Date of Patent: July 18, 2023Assignee: MITSUBISHI POWER, LTD.Inventors: Taro Tokutake, Ryuta Ito, Koichiro Iida, Yoshinori Wakita, Shuji Tanigawa
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Patent number: 11454130Abstract: A blade outer air seal includes a carrier that has a dovetail and a ceramic seal segment supported on the dovetail. The ceramic seal segment has first and second axial ends, first and second circumferential sides, an inner side, an outer side, and first and second inward-facing dovetail hooks that project from the outer side and define a dovetail key. The ceramic seal segment is axially receivable onto the dovetail of the carrier via the dovetail key.Type: GrantFiled: September 11, 2019Date of Patent: September 27, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William M. Barker, Thomas E. Clark, William Wangard, III, Danielle Mahoney
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Patent number: 11428106Abstract: 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: GrantFiled: September 17, 2018Date of Patent: August 30, 2022Assignee: SULZER MANAGEMENT AGInventors: Jozef H. G. Mattheij, Twan Antonius Martinus Althuizen
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Patent number: 11371363Abstract: 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: GrantFiled: June 4, 2021Date of Patent: June 28, 2022Assignee: General Electric CompanyInventors: Michael James Gutta, William Scott Zemitis
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Patent number: 11274561Abstract: 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: GrantFiled: September 17, 2018Date of Patent: March 15, 2022Assignee: SULZER MANAGEMENT AGInventors: Jozef H. G. Mattheij, Twan Antonius Martinus Althuizen
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Patent number: 11248620Abstract: 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: GrantFiled: September 18, 2019Date of Patent: February 15, 2022Assignee: Techtronic Cordless GPInventor: Koon For Chung
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Patent number: 11242762Abstract: 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: GrantFiled: November 21, 2019Date of Patent: February 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Alyson T. Burdette, Bryan P. Dube, Rutva A. Patel, Nicholas Broulidakis
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Patent number: 11078797Abstract: 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: GrantFiled: November 14, 2019Date of Patent: August 3, 2021Assignee: General Electric CompanyInventors: Rohit Chouhan, Shashwat Swami Jaiswal, Gunnar Leif Siden, Zachary James Taylor
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Patent number: 11073032Abstract: 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: GrantFiled: July 25, 2018Date of Patent: July 27, 2021Assignee: Rohr, Inc.Inventor: Teresa Kruckenberg
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Patent number: 10968747Abstract: 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: GrantFiled: December 18, 2013Date of Patent: April 6, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Eric D. Gray, Razvan Virgil Florea, Mark B. Stucky, Ray-Sing Lin
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Patent number: 10947980Abstract: 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: GrantFiled: February 2, 2016Date of Patent: March 16, 2021Assignee: Molten Metal Equipment Innovations, LLCInventor: Paul V. Cooper
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Patent number: 10934863Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials.Type: GrantFiled: November 13, 2018Date of Patent: March 2, 2021Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Daniel K. Morrison, Ted J. Freeman
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Patent number: 10895159Abstract: 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: GrantFiled: May 24, 2018Date of Patent: January 19, 2021Assignee: Safran Aircraft EnginesInventors: Vijeay Patel, Pragash Douglas, Quentin Bruno Guy Andre Emile Lievoux, Pauline Namvong
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Patent number: 10858947Abstract: 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: GrantFiled: February 24, 2017Date of Patent: December 8, 2020Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATIONInventors: Yuzo Tsurusaki, Yuki Nakamura, Yuichi Sasaki
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Patent number: 10781700Abstract: 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: GrantFiled: March 6, 2017Date of Patent: September 22, 2020Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATIONInventors: Nobuyori Yagi, Naoyuki Nagai, Shin Yanagisawa, Yuki Nakamura
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Patent number: 10767498Abstract: 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: GrantFiled: April 3, 2018Date of Patent: September 8, 2020Assignee: Rolls-Royce High Temperature Composites Inc.Inventor: Stephen Harris
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Patent number: 10738634Abstract: 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: GrantFiled: July 19, 2018Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventor: Scott H. Lamson
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Patent number: 10731481Abstract: 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: GrantFiled: November 1, 2016Date of Patent: August 4, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Daniel K. Vetters, Ted J. Freeman, James Glen Schwefel, Phil Bastnagel
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Patent number: 10669864Abstract: 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: GrantFiled: July 18, 2016Date of Patent: June 2, 2020Assignee: NUOVO PIGNONE SRLInventors: Giuseppe Iurisci, Angelo Grimaldi, Simone Corbo
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Patent number: 10669861Abstract: 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: GrantFiled: February 15, 2017Date of Patent: June 2, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Brandon Spangler, Dominic Mongillo
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Patent number: 10648346Abstract: 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: GrantFiled: July 6, 2016Date of Patent: May 12, 2020Assignee: General Electric CompanyInventors: Xiuzhang James Zhang, Kevin Richard Kirtley, Lisa DeBellis
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Patent number: 10641288Abstract: 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: GrantFiled: November 22, 2016Date of Patent: May 5, 2020Assignee: MTU Aero Engines AGInventors: Tim Schneider, Sergio Elorza Gomez
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Patent number: 10619484Abstract: 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: GrantFiled: July 22, 2016Date of Patent: April 14, 2020Assignee: General Electric CompanyInventors: Rohit Chouhan, Soumyik Kumar Bhaumik, Clint Luigie Ingram
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Patent number: 10590777Abstract: 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: GrantFiled: June 30, 2017Date of Patent: March 17, 2020Assignee: General Electric CompanyInventor: Robert Alan Brittingham
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Patent number: 10544687Abstract: 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: GrantFiled: July 10, 2017Date of Patent: January 28, 2020Assignee: MTU Aero Engines AGInventors: Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
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Patent number: 10508554Abstract: 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: GrantFiled: October 27, 2015Date of Patent: December 17, 2019Assignee: General Electric CompanyInventors: Rohit Chouhan, Shashwat Swami Jaiswal, Gunnar Leif Siden, Zachary James Taylor
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Patent number: 10502069Abstract: 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: GrantFiled: June 7, 2017Date of Patent: December 10, 2019Assignee: General Electric CompanyInventors: Mark Andrew Jones, Bradley Taylor Boyer
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Patent number: 10502073Abstract: 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: GrantFiled: March 9, 2017Date of Patent: December 10, 2019Assignee: General Electric CompanyInventors: Robert Edward Deallenbach, John James Ligos, Kristopher John Frutschy
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Patent number: 10486255Abstract: 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: GrantFiled: February 25, 2014Date of Patent: November 26, 2019Assignee: United Technologies CorporationInventor: William M. Rose
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Patent number: 10472974Abstract: 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: GrantFiled: February 14, 2017Date of Patent: November 12, 2019Assignee: General Electric CompanyInventors: Mark Andrew Jones, James Tyson Balkcum, III
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Patent number: 10443392Abstract: 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: GrantFiled: December 29, 2016Date of Patent: October 15, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Maxime Didier Delabriere, Laurent Patrick Coudert, Jean-Armand Marc Destouches, Daniel Marius Man
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Patent number: 10443393Abstract: 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: GrantFiled: December 29, 2016Date of Patent: October 15, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pascal Pierre Routier, Vincent Nicolas Leonardon, Daniel Marius Man, Guillaume Jochen Scholl
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Patent number: 10408063Abstract: 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: GrantFiled: March 30, 2016Date of Patent: September 10, 2019Assignee: ROLLS-ROYCE plcInventor: Stephen Christopher Diamond
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Patent number: 10385702Abstract: 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: GrantFiled: June 17, 2016Date of Patent: August 20, 2019Assignee: NAPIER TURBOCHARGERS LTDInventor: Neil Ryan Thomas
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Patent number: 10364703Abstract: 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: GrantFiled: November 4, 2014Date of Patent: July 30, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Sébastien Lionel Guingo, Joris Brousselle
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Patent number: 10344599Abstract: 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: GrantFiled: May 24, 2016Date of Patent: July 9, 2019Assignee: General Electric CompanyInventor: Fred Thomas Willett, Jr.
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Patent number: 10287901Abstract: 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: GrantFiled: November 11, 2015Date of Patent: May 14, 2019Assignee: United Technologies CorporationInventor: Andrew S. Aggarwala
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Patent number: 10253643Abstract: 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: GrantFiled: February 7, 2017Date of Patent: April 9, 2019Assignee: General Electric CompanyInventors: Daniel Patrick Kerns, Brandon ALlanson Reynolds
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Patent number: 10253638Abstract: 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: GrantFiled: August 12, 2015Date of Patent: April 9, 2019Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Santhosh Kumar Vijayan, Spencer Aaron Kareff
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Patent number: 10247007Abstract: 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: GrantFiled: May 2, 2017Date of Patent: April 2, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Neil Ristau, Mehmet Suleyman Ciray, Jason Douglas Herzlinger
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Patent number: 10202852Abstract: 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: GrantFiled: November 16, 2015Date of Patent: February 12, 2019Assignee: General Electric CompanyInventors: Shashwat Swami Jaiswal, Rohit Chouhan
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Patent number: 10138736Abstract: 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: GrantFiled: November 23, 2015Date of Patent: November 27, 2018Assignee: General Electric CompanyInventors: Rohit Chouhan, Sumeet Soni, Paul Kendall Smith, Srinivasa Govardhan Jayana, Sylvain Pierre, Harish Bommanakatte, Spencer Aaron Kareff
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Patent number: 10018066Abstract: 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: GrantFiled: September 23, 2015Date of Patent: July 10, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Philip Robert Rioux
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Patent number: 9957818Abstract: 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: GrantFiled: August 28, 2015Date of Patent: May 1, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Nicholas F. Martin, Jr., David J. Wiebe
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Patent number: 9915272Abstract: 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: GrantFiled: August 15, 2016Date of Patent: March 13, 2018Assignee: PIETRO ROSA T.B.M. S.R.L.Inventor: Andrea Maurizio
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Patent number: 9879549Abstract: 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: GrantFiled: May 3, 2012Date of Patent: January 30, 2018Assignee: SNECMAInventor: Laurent Gilles Dezouche
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Patent number: 9816380Abstract: 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: GrantFiled: March 6, 2014Date of Patent: November 14, 2017Assignee: General Electric Technology GmbHInventors: Michel Floch, Arnaud Buguin, Julien Lemaire
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Patent number: 9816382Abstract: 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: GrantFiled: February 28, 2014Date of Patent: November 14, 2017Assignee: Pietro Rosa T.B.M. S.r.l.Inventor: Andrea Maurizio
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Patent number: 9790802Abstract: 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: GrantFiled: May 11, 2012Date of Patent: October 17, 2017Assignees: SNECMA, HERAKLESInventors: Ivan Herraiz, Clement Roussille, Julien Mateo, Alain Allaria, Jean-Luc Soupizon
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Patent number: 9759070Abstract: 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: GrantFiled: August 28, 2013Date of Patent: September 12, 2017Assignee: General Electric CompanyInventors: Xiuzhang James Zhang, Melbourne James Myers, Robert Joseph Testa, Jr., Haiping Wang