With Diversely Oriented Inlet Or Additional Inlet For Diverse Fluid (e.g., Heating, Cooling Or Mixed Working Fluid, Etc.) Patents (Class 415/116)
  • Patent number: 10041353
    Abstract: A blade cascade of a turbomachine whose at least one side wall is configured to be circumferentially undulated and which has at least two elevations and at least one depression or at least two depressions having at least one elevation, as well as a turbomachine having a blade cascade of this kind.
    Type: Grant
    Filed: August 6, 2014
    Date of Patent: August 7, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Jochen Gier, Yavuz Guendogdu, Karl Engel
  • Patent number: 10036277
    Abstract: A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.
    Type: Grant
    Filed: June 12, 2013
    Date of Patent: July 31, 2018
    Assignee: SNECMA
    Inventors: Antoine Jean-Philippe Beaujard, Jacques Rene Bart
  • Patent number: 10036324
    Abstract: A turbine exhaust case frame (100) comprises an inner ring (104), an outer ring (102), and a plurality of load-bearing struts (106). The inner ring is configured to carry a load from inner bearings. The outer ring has installation bosses (116) with downward-facing mount surfaces (120). The load-bearing struts connect the inner ring to the outer ring.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Jonathan Ariel Scott, John J. Henderson, Ralph D. Harris
  • Patent number: 10030582
    Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: July 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Kevin Zacchera, Matthew Andrew Hough, Jonathan Lemoine, Christopher Treat, Alberto A. Mateo
  • Patent number: 10030523
    Abstract: An article for gas turbine engine includes a body that has a gaspath side for exposure in a core gaspath of a gas turbine engine. The gaspath side has an undulating surface. A cooling passage is in the body. The cooling passage has a undulating profile that corresponds to the undulating surface.
    Type: Grant
    Filed: February 13, 2015
    Date of Patent: July 24, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Tracy A. Propheter-Hinckley, Steven Bruce Gautschi
  • Patent number: 10018068
    Abstract: A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1 herein, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V. A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2 herein, wherein the Cartesian coordinates are provided with respect to a point P? which is at the center of an arc W? and co-planer with a machined surface V?.
    Type: Grant
    Filed: January 13, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter J. Milligan, Paul M. Lutjen, Ken F. Blaney, Thurman C. Dabbs, Kevin J. Ryan
  • Patent number: 10012147
    Abstract: An engine and particle decelerator is provided herein. The engine having: an inlet opening for directing air towards a compressor of the engine; and a particle decelerator located between the inlet opening and the compressor such that air travelling towards the compressor from the inlet opening must travel through the particle decelerator and wherein an area of the particle decelerator is greater than an inlet and an outlet of the particle decelerator.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: July 3, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Hoyt Y. Chang, Shayan Ahmadian
  • Patent number: 10012100
    Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend through the carrier to couple the annular runner with the carrier.
    Type: Grant
    Filed: January 6, 2016
    Date of Patent: July 3, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jun Shi, Jeffrey A. Walston, Aaron D. Sippel
  • Patent number: 9995217
    Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.
    Type: Grant
    Filed: February 3, 2014
    Date of Patent: June 12, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Enzo DiBenedetto
  • Patent number: 9988922
    Abstract: An impingement baffle for a gas turbine engine is provided. The impingement baffle is a one piece impingement ring with one opening and with fastening elements at both free ends of the impingement ring to enable the closing of the impingement ring. A gas turbine engine including at least one such an impingement baffle is also provided.
    Type: Grant
    Filed: September 16, 2010
    Date of Patent: June 5, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Johan Friis
  • Patent number: 9988928
    Abstract: System and methods for predicting a turbomachine engine safe start clearance following a shutdown of the turbomachine engine is provided. The system includes a controller operatively connected to a plurality of temperature detecting means (TDM). The TDMs are arranged at an upper and lower part of the engine casing, and are configured to sense parameters of the engine and to transmit the sensed parameters to the controller. The controller is configured to receive the sensed parameters and to determine, via a control application of the controller, whether components of the engine have sufficient clearance. The controller is further configured to transmit the clearance information, e.g., to a user. Based on the clearance information, the turbomachine engine is restarted.
    Type: Grant
    Filed: May 17, 2016
    Date of Patent: June 5, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Cristina C. Popescu, Michael J. Olejarski, Timothy E. Mazzotta
  • Patent number: 9988909
    Abstract: A turbocharger including a wheel having suction surfaces and hub surfaces contoured to reduce secondary flow. The suction surfaces are radially contoured with a sinusoidal component, and further have a chamfered edge at the shroud edge. The hub end-walls are contoured both streamwise and cross-stream with sinusoidal components.
    Type: Grant
    Filed: April 25, 2011
    Date of Patent: June 5, 2018
    Assignee: Honeywell International, Inc.
    Inventor: Cheng Xu
  • Patent number: 9982560
    Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: May 29, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark A. Boeke, Kristopher K. Anderson, Jeffrey J. De Gray, Jeffrey R. Levine, Sarah Riley, Richard M. Salzillo, Jr.
  • Patent number: 9982598
    Abstract: A variable bleed valve includes a variable bleed valve door disposed in a bleed inlet in transition duct and rotatable about an axis at or near a forward end of door. Valve is operable to open and close a bleed slot open to a booster bleed flowpath located outwardly of transition duct and having an airflow restrictor. Airflow restrictor may be variable such as a flapper valve. Booster bleed flowpath may pass through a bifurcated bleed duct including an inner passage radially bound by spaced apart inner and middle bleed walls and an outer passage radially bound by middle bleed wall and an outer bleed wall. Airflow restrictor may include an outlet area smaller than an inlet area of inner passage. Door seals against middle bleed wall to open inner passage and against outer bleed wall to open both passages.
    Type: Grant
    Filed: October 22, 2012
    Date of Patent: May 29, 2018
    Assignee: General Electric Company
    Inventors: Byron Andrew Pritchard, Jr., Charles Daniel Califf, Peter John Wood, Raymond Gust Holm, Allan George van de Wall, Peter Alfred Pezzi
  • Patent number: 9970452
    Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.
    Type: Grant
    Filed: February 17, 2015
    Date of Patent: May 15, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Michael Todd Barton, Yoseph Gebre-Giorgis, Harry Lester Kington, John Repp
  • Patent number: 9963996
    Abstract: A shroud cooling system configured to cool a shroud adjacent to an airfoil within a gas turbine engine is disclosed. The turbine engine shroud may be formed from shroud segments that include a plurality of cooling air supply channels extending through a forward shroud support for impingement of cooling air onto an outer radial surface of the shroud segment with respect to the inner turbine section of the turbine engine. The channels may extend at various angles to increase cooling efficiency. The backside surface may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels to provide enhanced cooling at the backside surface. The shroud cooling system may be used to slow down the thermal response by isolating a turbine vane carrier from the cooling fluids while still providing efficient cooling to the shroud.
    Type: Grant
    Filed: August 22, 2014
    Date of Patent: May 8, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Darryl Eng, Christopher Rawlings, Thomas Pechette, Friedrich T. Rogers, Jae Y. Um, Ching-Pang Lee
  • Patent number: 9963993
    Abstract: A turbine ring of a turbomachine is described, having a one-piece ring structure which has an outer ring which is continuous in the circumferential direction of the turbine ring and has a fastening section for fastening the turbine ring on a housing section of the turbomachine, an inner ring which is segmented in the circumferential direction and has a plurality of inner ring segments which are mutually displaceable in the circumferential direction for guiding the hot gas and has front sealing segments and rear sealing segments, as seen in the axial direction of the turbine ring, these sealing segments being spaced a distance apart from one another in the axial direction and extending between the inner ring and the outer ring, as well as a turbomachine having such a turbine ring.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: May 8, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Manfred Feldmann
  • Patent number: 9957900
    Abstract: One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: May 1, 2018
    Assignee: General Electric Company
    Inventors: Mehdi Milani Baladi, Edward Michael Yanosik, Jr., Richard Bradford Hook, Jr., Scott Edward Farley, Gordon Jeffery Follin
  • Patent number: 9957829
    Abstract: A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centerline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centerline relative to the nominal centerline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centerline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different center-lines.
    Type: Grant
    Filed: May 12, 2014
    Date of Patent: May 1, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventor: Andrew Shepherd
  • Patent number: 9951634
    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: June 11, 2015
    Date of Patent: April 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Carson A. Roy Thill, Russell E. Keene, Paul M. Lutjen
  • Patent number: 9952117
    Abstract: Methods for determining strain on turbine components include providing a turbine component comprising a plurality of strain sensor reference features disposed along the turbine component separated from one another by a plurality of first distances at a first time, reading the plurality of strain sensor reference features at a second time to determine a plurality of second distances between the plurality of strain sensor reference features, and comparing the plurality of second distances to the plurality of first distances to determine a plurality of non-linear strain measurements between the plurality of strain sensor reference features.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: April 24, 2018
    Assignee: General Electric Company
    Inventors: Gregory Lee Hovis, John David Ward, Jr., William Farris Ranson
  • Patent number: 9945244
    Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.
    Type: Grant
    Filed: August 13, 2015
    Date of Patent: April 17, 2018
    Assignee: General Electric Company
    Inventors: Frederic Woodrow Roberts, Victor John Morgan, Matthew Troy Hafner
  • Patent number: 9945247
    Abstract: An anti-icing system for an engine section stator of a gas turbine engine. The system includes an environmental control system pre-cooler heat exchange system and a conduit. The environmental control system pre-cooler heat exchange system is configured to exchange heat between air bled from a compressor of the engine and bypass duct air. The conduit is configured to exchange heat from the pre-cooler heat exchange system to a heat transfer medium. The conduit is also configured to transfer the heat from the heat transfer medium to the engine section stator.
    Type: Grant
    Filed: July 30, 2015
    Date of Patent: April 17, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Ajith Appukuttan, Benjamin Keeler, Paolo Vanacore
  • Patent number: 9938846
    Abstract: A turbine shroud for a gas turbine engine includes a plurality of shroud segments arranged around a central axis. Each shroud segment includes a carrier component, a blade track component, and a retainer component that couples the blade track component to the carrier component. The turbine shroud further includes a plurality of circumferential seals that seal circumferential interfaces between the shroud segments.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: April 10, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Aaron D. Sippel
  • Patent number: 9938904
    Abstract: A device and methods are provided for controlling a gas turbine engine based at least in part on real-time detection of spatially resolved temperature distributions of a turbine engine components. In one embodiment, a method includes detecting surface temperature of one or more blade elements, by an thermal probe, in a plurality of radial locations of an airfoil row to determine real-time spatially resolved surface temperature data for the one or more blade elements of the airfoil row, and controlling the engine based on the real-time spatially resolved surface temperature data.
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: April 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Jr., Charles W. Halderman
  • Patent number: 9932857
    Abstract: A bypass engine bearing holder (1) that holds an upstream bearing (6) and defines, with said upstream bearing, an oil chamber (100) and an air chamber (200), comprising a frusto-conical portion (11) defining an upstream bearing chamber (160) and a downstream inner chamber (150), and includes an outer collar (13) connected, by a weld (135), to a flange (15) that extends outward from the frusto-conical portion (11). The outer collar (13) has a sealable gimlet (131) engaging with the upstream bearing (6) such as to seal the oil chamber (100). The bearing holder (1) includes a plurality of oil recovery ducts (8) leading to the downstream inner chamber (150) and to the upstream bearing chamber (160). The oil recovery ducts (8) lead to the upstream bearing chamber (160), downstream from the weld (135) of the outer collar (13) on the flange (15), the weld (135) of the outer collar (13) being axisymmetric.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: April 3, 2018
    Assignee: SNECMA
    Inventors: Frederic Noel, Benoit Argemiro Matthieu Debray, Mario Cesar De Sousa, Gregory Ghosarossian-Prillieux, Nicolas Pommier
  • Patent number: 9920656
    Abstract: A barrier coating for isolating a metallic support component from a composite component in a gas turbine engine is provided. The barrier coating may be applied to the metallic support component so that when the ceramic component is mounted on the metallic support component the barrier coating is engaged.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: March 20, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Sean E. Landwehr, Sungbo Shim, Adam L. Chamberlain, Ann Bolcavage
  • Patent number: 9915204
    Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: March 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, James D. Hill
  • Patent number: 9879694
    Abstract: A gas turbine engine includes a fan section. A turbo-compressor section is connected to the fan section through a speed change mechanism.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: January 30, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: William G. Sheridan
  • Patent number: 9869202
    Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals (BOAS) disposed therein, the BOAS including a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in at least one of Table 1 and Table 2.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: January 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Carson A. Roy Thill, Dominic J. Mongillo, Jr., Kevin D. Tracy, Jeffrey A. Perry, Thurman C. Dabbs
  • Patent number: 9869196
    Abstract: An arcuate panel for a thermal control assembly includes an arcuate panel base, at least one axially extending panel header sealingly attached to a radially outwardly facing surface of the panel base, a plenum therebetween, one or more spray tubes or channels depending radially inwardly from the panel base and in fluid communication with the plenum, and radially outwardly biasing spring means mounted on or attached to the radially inwardly facing surface of the panel base. The panel may include at least one set of clockwise and counter-clockwise hinge wings attached to clockwise and counter-clockwise ends of the panel base, axial positioning, and circumferential positioning. The axial positioning may include a circular row of spring clips mounted on the panel base. A hoop of arcuate panels pivotably attached by hinges may encircle a portion of a casing compressing leaf springs against rings of the casing.
    Type: Grant
    Filed: May 12, 2015
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventors: Christophe Jude Day, Christopher Francis Poranski, James Edward Thompson, Jeffrey Scott Laubenthal, James L. Mazuk, Vernon Leroy Smith
  • Patent number: 9869201
    Abstract: The present application provides a seal for use between adjacent turbine components and with a cooling flow. The seal may include an impingement baffle top plate, a base plate, and one or more spacer elements therebetween. The cooling flow provides cooling through the impingement baffle top plate.
    Type: Grant
    Filed: May 29, 2015
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventors: Thomas Earl Dyson, Victor John Morgan, Neelesh Nandkumar Sarawate, David Benjamin Helmer
  • Patent number: 9863319
    Abstract: A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream. The thermal management system includes a metering device that is located near an outer diameter of the core engine. The metering device is configured to divide the cooling stream into multiple segregated passages. The metering device can be configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.
    Type: Grant
    Filed: March 1, 2013
    Date of Patent: January 9, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jorge I. Farah, Kalpendu J. Parekh
  • Patent number: 9856750
    Abstract: A mid-turbine frame for a gas turbine engine includes at least one spoke for connecting an outer frame case to an inner frame case. At least one spoke includes an inlet passage and at least two branches that extend transverse to the inlet passage.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: January 2, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Jorge I. Farah
  • Patent number: 9850913
    Abstract: An object is to position a plurality of guide vanes for generating swirl flow at a housing inner circumferential side in front of an impeller wheel to improve a surge margin and to restrict the decrease in a choke flow rate, thereby increasing an operation range of a compressor. A compressor 19 includes a compressor housing 15, an impeller wheel 7 which compresses intake gas flowing in from an intake-air inlet 23, a swirl-flow generating part including a plurality of guide vanes 55 disposed circumferentially along an inner circumferential wall of the intake-air channel 21 between the intake-air inlet 23 and the impeller wheel 7 and which swirls the intake gas from the intake-air inlet 23 around the rotational axis, and a central intake-air flow path 59 formed inside the guide vanes 55 to allow intake gas to flow to the impeller wheel 7 without passing through the guide vanes 55.
    Type: Grant
    Filed: August 24, 2012
    Date of Patent: December 26, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Byeongil An, Hiroshi Suzuki
  • Patent number: 9845696
    Abstract: A shroud sealing arrangement for a gas turbine engine, which comprises a static shroud assembly mounted to an engine case and having a platform surrounding a rotatable airfoil array. The platform has an inner side and an outer side and extends from a leading edge to a trailing edge. A shroud support structure mounts the shroud platform to the case. A circumferential groove is defined on the outer side of the shroud platform proximal to one of the leading edge and the trailing edge. A sealing ring is set in the groove and adapted to seal cooling air from escaping directly to the gas path.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: December 19, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Guy Lefebvre, Rene Paquet
  • Patent number: 9845691
    Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
    Type: Grant
    Filed: October 26, 2012
    Date of Patent: December 19, 2017
    Assignee: General Electric Company
    Inventors: Marshall Scott Allen, Victor Hugo Silva Correia, Robert Proctor, Jared Peter Buhler
  • Patent number: 9828880
    Abstract: A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: Henry Grady Ballard, Jr., Ozgur Bozkurt, Kenneth Damon Black, Radu Ioan Danescu
  • Patent number: 9822698
    Abstract: A centrifugal compressor for a turbocharger includes a passive or semi-passive inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position solely by aerodynamic forces on the mechanism. The inlet-adjustment mechanism includes a plurality of flexible vanes collectively forming a duct, and an effective diameter of the air inlet at the inducer portion of the compressor wheel is determined by a trailing edge inside diameter of the duct. The vanes are movable solely or in part by aerodynamic forces exerted on the vanes by the air flowing to the compressor wheel. The duct has a tapering configuration when the vanes are in a relaxed state, but under aerodynamic force the vanes flex outwardly and increase the trailing edge inside diameter of the duct, thereby increasing an effective diameter of the air inlet.
    Type: Grant
    Filed: February 6, 2015
    Date of Patent: November 21, 2017
    Assignee: Honeywell International Inc.
    Inventors: Hani Mohtar, Stephane Pees, Pascal Delapierre, William Joseph Smith, Pascal Villemin
  • Patent number: 9803501
    Abstract: A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.
    Type: Grant
    Filed: January 28, 2015
    Date of Patent: October 31, 2017
    Assignee: United Technologies Corporation
    Inventor: Cheng-Zhang Wang
  • Patent number: 9803491
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.
    Type: Grant
    Filed: December 31, 2012
    Date of Patent: October 31, 2017
    Assignee: United Technologies Corporation
    Inventors: Brian Ellis Clouse, David F. Cloud, Donna Clough
  • Patent number: 9803652
    Abstract: A centrifugal compressor having at least a diffuser is disclosed. The diffuser has an annular diffuser body having circumferentially spaced apart diffuser passages defining fluid paths through the diffuser body. The diffuser also has a plurality of diffusion members mounted to the annular diffuser body. Each diffusion member has a member inlet in fluid communication with a diffuser passage and a member outlet. Each diffusion member defines an aerodynamic throat disposed between the member inlet and the member outlet. The diffuser also has a fluid injection assembly with multiple injection conduits. Each injection conduit extends between a conduit inlet configured to receive a flow of compressible fluid from a supply and a conduit outlet communicating with a corresponding diffusion member downstream of the aerodynamic throat. The compressible fluid is injected through the conduit outlet into the diffusion members.
    Type: Grant
    Filed: February 10, 2014
    Date of Patent: October 31, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Hien Duong, Peter Townsend, Vijay Kandasamy, Koundinya Upadrasta
  • Patent number: 9790953
    Abstract: A multi or single-stage turbocompressor with at least one compressor wheel fastened to a shaft. The shaft is mounted in a turbocompressor housing which, behind the hub disc of the compressor wheel, includes an interior housing region as well as in front of the hub disc of the compressor wheel a front interior housing region. The driven compressor wheel delivers a fluid from an inlet channel to an outlet channel. The front interior housing region includes a wheel lateral space from which an extraction channel for the extraction of fluid is provided.
    Type: Grant
    Filed: April 15, 2008
    Date of Patent: October 17, 2017
    Assignee: MAN Diesel & Turbo SE
    Inventors: George Kleynhans, Peter Ortmann, Roger Suter
  • Patent number: 9770693
    Abstract: A homogenization apparatus for at least two fluid flows for homogeneous gas/air mixing in a gas engine, in which at least two fluid feed lines conducting different fluid flows and one fluid outflow line conducting the homogenized fluid are connected to a central homogenization space as mixing region. In a connection region upstream of the homogenization space, the fluid feed lines have in each case one line section with a flow deflection in one direction with a flow deflection which follows downstream in the other direction and are connected in such a way that the fluid flows are fed tangentially to the homogenization space with a swirl movement imparted to them, in such a way that a rotating, turbulent flow which assists the homogenization process is formed in the homogenization space.
    Type: Grant
    Filed: March 23, 2015
    Date of Patent: September 26, 2017
    Assignee: MAN TRUCK & BUS AG
    Inventors: Bruno Barciela, Joachim Weiβ
  • Patent number: 9759088
    Abstract: A turbomachine separator including a device for de-icing the turbomachine separator, and a distribution element, wherein the separator is formed by an inner ferrule and an outer ferrule, wherein the inner ferrule is fitted with a first mounting flange and a second mounting flange, the de-icing device including an internal air supply duct, able to inject air into the separator, wherein the internal supply duct is connected to an air inlet, wherein the air inlet forms a projection external to the de-icing device, allowing a flexible connection with a tube of the distribution element for conveying hot air, a first fastener constructed and arranged to be attached to the first mounting flange; and a second fastener constructed and arranged to be attached to the second mounting flange.
    Type: Grant
    Filed: May 15, 2012
    Date of Patent: September 12, 2017
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jacques René Bart
  • Patent number: 9752587
    Abstract: The present disclosure relates to shroud bleed in centrifugal compressors. An air-limiting component 130 may be located adjacent to a shroud 120. The shroud 120 may have a primary bleed slot 210, and the air-limiting component 130 may have a secondary bleed slot 310. The primary bleed slot 210 and the secondary bleed slot 310 may overlap at an effective bleed slot location. The air-limiting component 130 may rotate relative to the shroud 120, which may change a streamwise location of the effective bleed slot.
    Type: Grant
    Filed: June 11, 2014
    Date of Patent: September 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Benjamin E. Fishler
  • Patent number: 9732885
    Abstract: A cooling device for the casing of a jet engine, includes a cooling tube and a supporting device, the supporting device including an attachment plate and an attachment clamp, the attachment clamp including a clamp body surrounding the cooling tube and an attachment element attached to the attachment plate, wherein the attachment plate includes: an opening; and an attachment tab secured to the main wall of the attachment plate and arranged on at one portion of the periphery of the opening, the attachment clamp passing through the opening, and the attachment element of the attachment clamp being attached to the attachment tab.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: August 15, 2017
    Assignee: SNECMA
    Inventors: Arthur Cohin, Baghdad Achbari, Audrey Charrie, Aurélien René-Pierre Massot
  • Patent number: 9683444
    Abstract: An air hot part of a gas turbine engine, the hot part having an isogrid formed on a cool surface opposite to a hot surface, where an impingement plate bonded over multiple impingement cooling surfaces of the airfoil, where the impingement plate forms a series of double or triple impingement cooling for separate surfaces of the airfoil. The impingement plate can be shaped and sized to fit over an airfoil surface that requires multiple impingement cooling.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: June 20, 2017
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Russell B Jones
  • Patent number: 9677475
    Abstract: A gas turbine engine includes a turbine section that includes a turbine rotor arranged in a plenum. A compressor section includes a compressor rotor assembly that has spaced apart inner and outer portions that provide an axially extending cooling channel. Compressor blades extend radially outward from the outer portion which provides an inner core flow path. A rotor spoke is configured to receive a first cooling flow and fluidly connect the outer portion to the cooling channel. The compressor rotor assembly has a coolant exit that is in fluid communication with the cooling channel. The compressor rotor assembly is configured to communicate the first cooling flow to the turbine rotor. A bleed source is configured to provide a second cooling flow. A combustor section includes an injector in fluid communication with the bleed source. The tangential onboard injector is configured to communicate the second cooling flow to the turbine rotor.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: June 13, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Patent number: 9677423
    Abstract: An aft hub sealing assembly for a gas turbine engine is disclosed. The aft hub sealing assembly includes an aft hub, a bearing cap, an aft baffle, a first seal, and a second seal. The aft hub includes a body portion and a disk portion aft surface. The bearing cap includes a bearing cap inner portion spaced apart from the body portion. The aft baffle is located adjacent the disk portion. The aft baffle includes a baffle forward surface following a contour of the disk portion aft surface. The first seal is between the bearing cap inner portion and the body portion. The second seal is between the bearing cap inner portion and the body portion.
    Type: Grant
    Filed: June 20, 2014
    Date of Patent: June 13, 2017
    Assignee: Solar Turbines Incorporated
    Inventor: Leslie John Faulder