With Heating, Cooling Or Thermal Insulation Means Patents (Class 416/95)
  • Patent number: 11174846
    Abstract: A multilayer protective covering can protect a surface from lightning strikes. The covering includes a bottom conductive layer affixed to the surface and having a first opening that is aligned with a grounding connection so that the grounding connection is exposed through first opening and not in contact with the bottom conductive layer. The covering also includes a dielectric layer affixed to the bottom conductive layer and having second opening aligned with the grounding connection so that the grounding connection is exposed through second opening and not in contact with the dielectric layer. The covering additionally includes a top conductive layer affixed to the dielectric layer and covering the grounding connection. The top conductive layer directs electrical current from a lightning strike on the surface to the grounding connection.
    Type: Grant
    Filed: May 7, 2018
    Date of Patent: November 16, 2021
    Assignee: Wichita State University
    Inventor: Billy Marvin Martin
  • Patent number: 11174735
    Abstract: Shaft assemblies, turbomachines, and methods of servicing a turbomachine are provided. A shaft assembly includes a first shaft having a first rabbet annularly defined therein. The first rabbet includes a first axially extending face and a first radially extending face. A second shaft coupled to the first shaft. The second shaft includes a second rabbet annularly defined therein and positioned opposite the first rabbet. The second rabbet includes a second axially extending face and a second radially extending face. A patch ring is mounted between the first rabbet and the second rabbet. The patch ring includes a main body positioned between and in contact with the first axially extending face and the second axially extending face. A first arm extends radially outward from the main body, and a second arm extends radially inward from the main body.
    Type: Grant
    Filed: December 23, 2019
    Date of Patent: November 16, 2021
    Assignee: General Electric Company
    Inventors: Matthew Ryan Ferslew, Katherine Courtlyn MacManus, Srinivas Ravi, John Herbert Dimmick, Jonathan Michael Webster, Gang Liu
  • Patent number: 11174746
    Abstract: A stator vane for a steam turbine includes: a vane body having an airfoil cross section including a pressure-side partition wall having a concave surface shape and a suction-side partition wall having a convex surface shape, the vane body having a hollow section formed between an inner surface of the pressure-side partition wall and an inner surface of the suction-side partition wall; and a first division wall dividing the hollow section into a first hollow section positioned at a leading edge side and a second hollow section positioned at a trailing edge side. The first hollow section is configured to be supplied with a fluid, or as a sealed space, and a slit is formed on at least one of the pressure-side partition wall or the suction-side partition wall, the slit being in communication with the second hollow section.
    Type: Grant
    Filed: February 5, 2020
    Date of Patent: November 16, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Nao Taniguchi, Ryo Takata, Tsuyoshi Kitamura, Yuichiro Hirano
  • Patent number: 11168615
    Abstract: A double ring axial seal for a disk and blade; the disk including an array of blade slots at a perimeter of the disk configured to receive a root portion of the blade, the blade includes a platform located between the root portion and an airfoil extending from the platform opposite the root portion, the platform including a receiver with an overhang proximate the root portion and the platform including a hook opposite the receiver proximate the root portion; a disk slot formed on a first side of the disk proximate the array of blade slots; a first axial seal ring coupled with the disk slot and the receiver; the first axial seal ring having a cutout proximate an outer perimeter of the first axial seal ring, the cutout sized to receive the overhang of the blade platform.
    Type: Grant
    Filed: August 25, 2020
    Date of Patent: November 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: William S. Pratt
  • Patent number: 11118461
    Abstract: A second outer surface (49ab) of a top plate (49) is recessed from a first outer surface (49aa) of the top plate (49) in the direction away from the inner peripheral surface (34a) of a turbine casing (34) so that a step (50) is formed between the second outer surface (49ab) and the first outer surface (49aa). At least part of the discharge opening (53B) of a cooling hole (53) is disposed in the second outer surface (49ab). The cooling hole (53) extends so as to be tilted relative to the second outer surface (49ab) so that the cooling hole (53) discharges a cooling medium to the upstream side of a combustion gas flowing between the second outer surface (49ab) and the inner peripheral surface (34a) of the turbine casing (34).
    Type: Grant
    Filed: March 27, 2019
    Date of Patent: September 14, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Ryuta Ito, Koichiro Iida
  • Patent number: 11105205
    Abstract: A rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically to the rotor axis inside the rotor shaft. The rotor shaft further includes a plurality of cooling bores extending radially outward from the rotor cavity to feed cooling air into an internal cooling system in a blade. Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portion ends in a plateau, projecting above the outer circumference contour of the rotor cavity. Thus, cooling bore inlets are shifted to a low stress area and the lifetime of the rotor is improved.
    Type: Grant
    Filed: July 25, 2014
    Date of Patent: August 31, 2021
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Steffen Holzhaeuser, Daniel Eckhardt, Sergei Riazantsev, Torsten Winge
  • Patent number: 11098646
    Abstract: A gas turbine engine is provided, with a compressor section including a fan driven by an engine shaft about a rotation axis, the engine shaft defining a bore extending axially therethrough from a hot gas inlet to a hot gas outlet, the hot gas inlet located downstream of the compressor section, a nose cone mounted to the fan and defining a cavity therewithin, a first impeller and a second impeller mounted within the cavity, the first impeller having an inlet facing a forward direction of the gas turbine engine, the inlet of the first impeller in fluid flow communication with an air inlet defined in an outer surface of the nose cone, the second impeller having an inlet facing a rearward direction of the gas turbine engine, the inlet of the second impeller being in fluid flow communication with the hot gas outlet of the engine shaft.
    Type: Grant
    Filed: July 8, 2019
    Date of Patent: August 24, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Enzo Macchia, Daniel Alecu, Sean Downard, David Hill
  • Patent number: 11078843
    Abstract: A gas turbine engine includes a fan rotor, a compressor section, a combustor section, and a turbine section. The turbine section is positioned downstream of the combustor section. A fan drive turbine in the turbine section, and a shaft connects the fan drive turbine to the fan rotor. An inlet duct is connected to a cooling air source and connected to a cooling compressor downstream of the fan drive turbine. The cooling compressor is connected to an air source, and connected to a turning duct for passing compressed air in an upstream direction through the shaft. A method is also disclosed.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: August 3, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Gary D. Roberge, Jorn Axel Glahn
  • Patent number: 11066936
    Abstract: A sealing plate for sealing cooling passages in a cooled turbine blade of a gas turbine engine and directing and controlling air flow through cooling passages is provided.
    Type: Grant
    Filed: May 7, 2020
    Date of Patent: July 20, 2021
    Assignee: Rolls-Royce Corporation
    Inventor: Cameron Crenshaw
  • Patent number: 11053807
    Abstract: An axial flow rotating machine includes: a rotor; a plurality of vanes; and a medium flow modification member. Each of the vanes has an inner shroud and one or more seal fins. An annular groove, which is recessed toward a radially inner side, in which the inner shroud and the seal fins are placed in a non-contact manner, is formed at a rotor shaft. A distance from an end of the inner shroud on a furthest axially downstream side to a downstream-side groove side surface is a distance (L). A distance (Lf) from a most-downstream seal fin to a medium flow modification surface is equal to or less than the distance (L) in the axially downstream side.
    Type: Grant
    Filed: June 6, 2018
    Date of Patent: July 6, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kazuhiro Momma, Shigeki Senoo
  • Patent number: 11021974
    Abstract: A wheel assembly for a gas turbine engine includes a disk, an annular coverplate, and an anti-rotation feature. The disk is adapted to receive blades and rotate about an axis during use of the gas turbine engine. The annular coverplate is coupled with the disk and adapted to block axial movement of the blades. The anti-rotation feature is coupled with the disk and the annular coverplate to resist rotation of the annular coverplate relative to the disk.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: June 1, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, James Sellhorn
  • Patent number: 10968745
    Abstract: A turbine, a gas turbine, and a method of disassembling turbine blades, capable of ensuring stable sealing performance as well as facilitating disassembly of turbine blades are provided. The turbine may include a rotor disk including a plurality of slots formed therein, a plurality of turbine blades spaced apart from each other by a predetermined distance in a circumferential direction of the rotor disk on an outer peripheral surface, each of the turbine blades being inserted into an associated one of the slots, and a retainer sealing a cooling passage defined between the rotor disk and the turbine blade, wherein the turbine blade includes an airfoil-shaped blade part, a root part inserted into the rotor disk, and a platform part located between the blade part and the root part, and the root part includes a blade hook protruding therefrom to support the retainer.
    Type: Grant
    Filed: July 9, 2019
    Date of Patent: April 6, 2021
    Inventor: Victor Shemyatovskiy
  • Patent number: 10934865
    Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of the airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar includes standoffs, and a cover panel is bonded to an outer surface of the standoffs to define passages between the cover panel and the spar. Cooling air is fed through an inlet port formed in a base standoff to the passages of the spar through a cooling feed channel defined in the disk or shank portion.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: March 2, 2021
    Assignee: Rolls-Royce Corporation
    Inventor: Matthew T. Kush
  • Patent number: 10934861
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc.
    Inventors: Sachin Dhiwar, Ted J. Freeman, Thomas Martin
  • Patent number: 10830146
    Abstract: A cooling system configured to cool aspects of the turbine engine between a compressor and a turbine assembly is disclosed. In at least one embodiment, the cooling system may include one or more mid-frame cooling channels extending from an inlet through one or more mid-frame torque discs positioned downstream of the compressor and upstream of the turbine assembly. The inlet may be positioned to receive compressor bleed air. The mid-frame cooling channel may be positioned in a radially outer portion of the mid-frame torque disc to provide cooling to outer aspects of the mid-frame torque disc such that conventional, low cost materials may be used to form the mid-frame torque disc rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel in the mid-frame torque disc may be exhausted into a cooling system (10) for the downstream turbine assembly.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: November 10, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Yan Yin, Robert W. Sunshine, Kok-Mun Tham, Todd A. Ebert, Kevin M. Light, Ernie B. Campbell
  • Patent number: 10822961
    Abstract: A turbomachine blade including a hollow body defining a cavity, and including a downstream trailing edge. The blade further includes at least one hole which communicates with the cavity and which opens downstream onto the trailing edge. The trailing edge extends along the main radial direction of the blade, and including a downstream convex face. The blade is characterised in that each hole opens onto a planar rear face of a flat region formed in the trailing edge.
    Type: Grant
    Filed: July 1, 2016
    Date of Patent: November 3, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Laurent Patrick Robert Coudert, Erwan Daniel Botrel
  • Patent number: 10822952
    Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.
    Type: Grant
    Filed: September 17, 2014
    Date of Patent: November 3, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Jeffrey S. Beattie, Jason D. Himes, Matthew Andrew Hough, Christopher Corcoran
  • Patent number: 10794188
    Abstract: A rotor blade assembly group for an engine with a ring-shaped or disc-shaped blade carrier having multiple rotor blades that are provided along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blades, the carrier section comprises a connection area, at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the first stiffening element is arranged at a first face side of the blade carrier and the second stiffening element is arranged at a second face side that is facing away from the first face side. The first and second stiffening elements are connected to the connection area of the blade carrier and in addition are connected to each other.
    Type: Grant
    Filed: October 11, 2017
    Date of Patent: October 6, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Miklos Gaebler, Sven Brueggmann
  • Patent number: 10794199
    Abstract: A rotor blade assembly group for an engine with at least one blade carrier having at least one rotor blade that is provided with multiple rotor blades along a circle line about a central axis of the rotor blade assembly group, wherein the blade carrier has a carrier section that extends radially inwards in the direction of the central axis with respect to the rotor blade, the carrier section comprises a connection area at which a stiffening structure with at least two, first and second, stiffening elements is fixedly attached, and the stiffening element is arranged at a first face side of the blade carrier, and the second stiffening element is arranged at a second face side that is facing away from the first face side. The blade carrier is formed in a ring-segment-shaped or disc-segment-shaped-manner.
    Type: Grant
    Filed: October 11, 2017
    Date of Patent: October 6, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Miklos Gaebler, Sven Brueggmann
  • Patent number: 10753212
    Abstract: A turbine blade, installed on a rotor disk of a turbine and configured to rotate the turbine by a force of flowing gas, includes a root configured to be coupled to the rotor disk; a platform integrally formed with an upper portion of the root, the platform having opposite sides respectively extending in an axial direction of the rotor disk; an airfoil integrally formed with an upper portion of the platform; and an angel wing configured to be removably coupled to each of the opposite sides of the platform. When coupled, the angel wing protrudes from the platform in the axial direction. The turbine blade, which may be included in the turbine of a gas turbine, is capable of improving the castability and adjusting a clearance between an airfoil and a turbine rotor disk such that space between the airfoil and the turbine rotor disk can be reliably sealed.
    Type: Grant
    Filed: July 9, 2018
    Date of Patent: August 25, 2020
    Assignee: Doosan Heavy Industries & Construction Co., Ltd
    Inventor: Jin Woo Song
  • Patent number: 10753230
    Abstract: A spoolie manifold including two or more spaced apart caps including outlets and one pair of caps connected together in flow communication by a jumper tube assembly. Jumper tube assembly including a jumper tube having first and second spoolies attached to opposite ends of the jumper tube. Ends may be welded into counterbores of the spoolies having spherical spoolie ends press-fitted into first and second sleeves in bores in pair of the caps and sleeves retained in bores with retainer clips. A duct connected in flow communication to an inlet of one of the caps. Spoolie manifold may include three spaced apart caps including a distributor cap between two port caps connected in flow communication to distributor cap by jumper tube assembly. Cap outlets may be feed strut ports in casing of turbine frame including hub spaced inwardly from casing and having spaced apart hollow struts with strut ports.
    Type: Grant
    Filed: November 14, 2018
    Date of Patent: August 25, 2020
    Assignee: General Electric Company
    Inventors: John Alan Manteiga, Sydney Michelle Wright, Christopher Richard Koss, Tod Kenneth Bosel
  • Patent number: 10677226
    Abstract: Cooling a wind turbine generator It is described an arrangement (100, 200) for cooling a generator mounted in a nacelle of a wind turbine, the arrangement comprising: a cooling air inlet (105) at an outer wall (1?7) of the nacelle (103) for introducing cooling air (109) into a space region (111) inside the nacelle; an inlet fan (113) downstream the cooling air inlet (105) configured to pressurize the introduced cooling air within the space region (111); a filter system (115) downstream the inlet fan (113) and separating the space region (111) from another space region (117) inside the nacelle (103), the other space (117) region being in communication with generator portions (119) to be cooled; a duct system (129) adapted to guide a portion (130) of cooling air (132) heated by exchange of heat from the generator portions to the cooling air into the space region (111).
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: June 9, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Peter Hessellund Soerensen
  • Patent number: 10648349
    Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).
    Type: Grant
    Filed: March 8, 2018
    Date of Patent: May 12, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventors: Andrew Hewitt, Ian W R Harrogate
  • Patent number: 10641174
    Abstract: A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.
    Type: Grant
    Filed: January 18, 2017
    Date of Patent: May 5, 2020
    Assignee: General Electric Company
    Inventors: Debabrata Mukhopadhyay, Sanjeev Kumar Jain, Sendilkumaran Soundiramourty, Rajesh Mavuri, Jagdish Prasad Tyagi
  • Patent number: 10641110
    Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a number of blade posts, tabs and slots circumferentially disposed about a rim portion of the disk. The tabs each include a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion. The blade posts, tabs and slots are circumferentially oriented about the rim portion such that a tab or slot is positioned radially inward of each blade post.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: May 5, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jeffrey Leon, William Indoe, Brian J. Burke, Kimberly Caruso, Santiago Orellana, Kurt Leach, Fabian D. Betancourt
  • Patent number: 10550702
    Abstract: A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jeffrey Leon, William Indoe, Kimberly Caruso, Brian J. Burke, Kurt Leach, Fabian D. Betancourt
  • Patent number: 10487674
    Abstract: A securing device for a turbine blade wherein the securing device prevents the turbine blade from moving radially and axially and includes a retaining piece that includes a projection which extends into a recess in the root of the turbine blade and which prevents the blade from moving axially.
    Type: Grant
    Filed: January 5, 2016
    Date of Patent: November 26, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventor: Andreas Rehnsch
  • Patent number: 10472969
    Abstract: A cooling structure for a turbine includes a plurality of disks configured to rotate integrally with blades, the disks being arranged along a rotational axis; and the disks have disk holes defined therein and arranged in a circumferential direction for supplying cooling air for cooling the blades to downstream disks. At least one of the disk holes is set such that, when a rotational direction of the disk is defined as a positive direction and a direction opposite the rotational direction is defined as a negative direction, an outlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an outlet of the disk hole is smaller than an inlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an inlet of the disk hole.
    Type: Grant
    Filed: September 7, 2015
    Date of Patent: November 12, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Daigo Fujimura
  • Patent number: 10393428
    Abstract: The invention relates to a device for cooling and/or liquefying, at a low-temperature, a working fluid containing helium or consisting of pure helium. The device includes a working circuit provided with a compressor station and a cold box. The compressor station includes one or more compression stages, each using one or more compressors that include a compressor wheel rigidly connected to an axle that is rotatably mounted on bearings. The axle of each compressor is rotated by an output shaft of a motor via a gear mechanism placed in a mechanical housing including lubricating oil. Said device is characterized in that the inner space of the mechanical housing contains a gaseous atmosphere consisting of a gaseous mixture having a mean molar mass that smaller than the molar mass of the air.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: August 27, 2019
    Assignee: L'Air Liquide Societe Anonyme Pour L'Etude Et L'Exploitation Des Procedes Georges Claude
    Inventors: Jean-Marc Bernhardt, Fabien Durand
  • Patent number: 10316751
    Abstract: a gas turbine engine structure includes a body radially spanning an inner portion and an outer portion. The structure body includes a first passage interior to the structure body. The first passage includes a first opening on one of a radially outward edge and a radially inward edge of the structure, and a second opening on the other of the radially outward edge and the radially inward edge of the structure. A second passage is also included interior to the structure. The second passage is approximately aligned with the first passage, and is disposed between the first passage and one of the first surface and the second surface of the structure. The second passage insulates the first passage from heat transfer through one of the first surface and the second surface.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: June 11, 2019
    Assignee: United Technologies Corporation
    Inventors: Benjamin F. Hagan, Ryan Alan Waite
  • Patent number: 10247015
    Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar is hollow, and a cover panel is bonded to an outer surface of standoffs to define passages between the cover panel and the spar. Cooling air is fed to the hollow spar through a cooling feed channel defined in the disk or shank portion.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: April 2, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Matthew T. Kush, Douglas D. Dierksmeier
  • Patent number: 10233761
    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: March 19, 2019
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Gregory Thomas Foster, Joseph Anthony Weber, James Fredric Wiedenhoefer
  • Patent number: 10190422
    Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: January 29, 2019
    Assignee: Solar Turbines Incorporated
    Inventors: Luzeng Zhang, Juan Yin, Hee Koo Moon
  • Patent number: 10156244
    Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: December 18, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Roy D. Fulayter, Jonathan M. Rivers
  • Patent number: 10072585
    Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
    Type: Grant
    Filed: March 10, 2014
    Date of Patent: September 11, 2018
    Assignee: United Technologies Corporation
    Inventors: John H. Mosley, James P. Chrisikos, John J. O'Connor, Charles C. Wu, David Glasspoole, Roger Gates
  • Patent number: 10036255
    Abstract: A platform cooling device directs a cooling fluid onto a root side of a platform of a turbomachine part. The platform cooling device includes a first segment to be positioned at a root of the turbomachine part and a second segment, at an angle to the first segment, to be positioned at the root side of the platform of the turbomachine part. The second segment may include at least one impingement channel having an inlet for receiving at least a part of the cooling fluid and an outlet for releasing the received cooling fluid onto the root side of the platform. The first segment and the second segment may define a path for the cooling fluid via the impingement channel. A turbomachine component includes the platform cooling device.
    Type: Grant
    Filed: March 18, 2014
    Date of Patent: July 31, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Janos Szijarto, Lieke Wang
  • Patent number: 9869185
    Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Stephen Mark Molter, Mark Edward Stegemiller, Nicholas Ertel, Vanessa Camarillo
  • Patent number: 9835139
    Abstract: In order to maximize cooling while minimizing drag in aerial vehicles of airborne wind turbines, it may be preferable to dissipate the cooling energy of the motors via a radiator in a region with advantageous airflow parameters. Aerial vehicle rotors operating in thrust mode may produce relatively more airflow velocity in certain regions further away from the center of the rotor blades, both radially and longitudinally. Placing a radiator in a rotor-supporting pylon and offset from the center of the rotor blades and aft of the rotor blades may allow for greater cooling while the aerial vehicle while in thrust mode.
    Type: Grant
    Filed: March 10, 2014
    Date of Patent: December 5, 2017
    Assignee: X Development LLC
    Inventor: Damon Vander Lind
  • Patent number: 9810234
    Abstract: A fan impeller for the conveyance of a gaseous fluid includes several blades arranged with constant angular spacing around a rotation axis. At least one blade has a boundary zone and an inner zone, together with a bead extending between them along a curved path and/or the boundary zone is determined by a first blade surface and the inner zone is determined by a second blade surface, which are arranged with varying geometry.
    Type: Grant
    Filed: September 10, 2014
    Date of Patent: November 7, 2017
    Assignee: Punker GmbH
    Inventors: Henning Bähren, Christian Hornhardt, Matthias Wolf, Yingan Xia
  • Patent number: 9810072
    Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: November 7, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Zhirui Dong, Xiuzhang James Zhang, Jason Adam Neville
  • Patent number: 9770785
    Abstract: A system for forming a cooling hole in an airfoil includes a liquid-jet guided laser. The liquid-jet guided laser generates a laser beam confined within a fluid column. The fluid column/laser beam is directed at an outer surface of the airfoil. The system also includes a purge medium supply that is fluidly coupled to an aperture of the airfoil. The purge medium supply provides a purge medium into an inner cavity of the airfoil. The purge medium flow is oriented to flow in a flow direction that is substantially parallel to an inner surface of the cavity. A cooling hole is formed in the airfoil and extends through the outer surface and penetrates the inner surface of the cavity. A centerline of the cooling hole forms an acute angle with respect to the purge medium flow direction. The system described herein provides a method for manufacturing an airfoil.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: September 26, 2017
    Assignee: General Electric Company
    Inventors: Zhaoli Hu, Abe Denis Darling, Shamgar Elijah McDowell, Douglas Anthony Serieno
  • Patent number: 9670784
    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side.
    Type: Grant
    Filed: October 23, 2013
    Date of Patent: June 6, 2017
    Assignee: General Electric Company
    Inventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio, Jacob Charles Perry, II
  • Patent number: 9382802
    Abstract: A compressor rotor is provided having a rotor blade groove thereon and also includes a device for cooling the rotor in the region of a compressor rotor exit. Efficient cooling is achieved by the compressor rotor, in a compressor rotor exit region, having a ring which is pushed concentrically, and at a distance, forming a gap, over a rotor disk of the rotor, and is fastened on the disk, by the rotor blades, in the compressor rotor exit region, being inserted into corresponding grooves on the ring and being retained there, by first means for directing an axial flow of cooling medium from the compressor rotor exit through the ring, and by second means for deflecting the cooling medium which issues from the ring such that the cooling medium flows back in the axial direction through the gap between the ring and the rotor disk, encompassed by the ring.
    Type: Grant
    Filed: July 24, 2012
    Date of Patent: July 5, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Christian Dombek, Mauro Corradi
  • Patent number: 9243504
    Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.
    Type: Grant
    Filed: December 30, 2013
    Date of Patent: January 26, 2016
    Assignee: United Technologies Corporation
    Inventors: Seth J. Thomen, Christopher Corcoran
  • Patent number: 9217334
    Abstract: The present application provides a cover plate assembly for use with a rotor disk. The cover plate assembly may include a radial flange extending from the rotor disk, a flange aperture extending through the radial flange, a cover plate segment with a fastening aperture and a hook for receiving the radial flange, and a fastener extending through the flange aperture and the fastening aperture.
    Type: Grant
    Filed: October 26, 2011
    Date of Patent: December 22, 2015
    Assignee: General Electric Company
    Inventors: John Wesley Harris, Jr., Gary Charles Liotta
  • Patent number: 9188008
    Abstract: In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.
    Type: Grant
    Filed: December 21, 2011
    Date of Patent: November 17, 2015
    Assignee: Avio S.p.A.
    Inventors: Daniele Coutandin, Massimiliano Albani
  • Patent number: 9181805
    Abstract: A bladed rotor of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages, each one defined by a turbine disk on one side and by a root of a corresponding blade coupled to this turbine disk on the other, the incoming air of each passage being subdivided into two or more airflows and each flow being directed towards the turbine disk in a predefined direction.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: November 10, 2015
    Assignee: AVIO S.p.A.
    Inventors: Daniele Coutandin, Stefano Zecchi
  • Patent number: 9181810
    Abstract: A system includes a cover segment set configured to mount in first and second grooves circumferentially along a blade mounting region of a turbine rotor. The cover segment set includes a seal segment and a cover segment. The seal segment has a seal body with a lock feature, wherein the seal segment is configured to mount circumferentially along the second groove. The cover segment includes first and second lips extending along first and second circumferential portions of a cover body. The first and second lips are at an offset from one another. The first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove adjacent the seal segment, and the second lip includes a mating lock feature configured to couple with the lock feature of the seal body.
    Type: Grant
    Filed: April 16, 2012
    Date of Patent: November 10, 2015
    Assignee: General Electric Company
    Inventors: John Herbert Dimmick, III, Raymond Joseph Lecuyer, Norman K. Austin
  • Patent number: 9175566
    Abstract: A gas turbine engine preswirler (470) includes an outer ring (471) and an inner ring (472). The inner ring (472) includes a plurality of angled holes (490). Each angled hole (490) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular a radial from an axis of the preswirler (470). The component of the angle is angled relative to an axial direction of the preswirler (470).
    Type: Grant
    Filed: September 26, 2012
    Date of Patent: November 3, 2015
    Assignee: Solar Turbines Incorporated
    Inventors: Hongzhou Xu, Michael D. Fox, Scott L. Stafford, Edward T. Ramirez
  • Patent number: 9151274
    Abstract: A wind turbine has a nacelle wherein a component is equipped with a first temperature sensor for detecting a temperature of the component, a second temperature sensor for detecting an outside temperature inside or outside the nacelle, a heater associated with a component to heat the latter, and a heater controller. The detected temperature of the component and the detected outside temperature are provided as input signals to the heater controller which activates the heater for heating when the detected temperature of the component is below a predetermined switch-on value for the heater. The switch-on value for the heater is, in at least one predetermined temperature interval, dependent on the detected outside temperature. The switch-on value for a first outside temperature is greater than the switch-on value for a second outside temperature in the temperature interval when the second outside temperature is greater than the first outside temperature.
    Type: Grant
    Filed: March 9, 2012
    Date of Patent: October 6, 2015
    Assignee: Nordex Energy GmbH
    Inventors: Moritz Dreher, Lars Scheibig, Frederic Radou