Reaction Engine Type Patents (Class 181/213)
  • Patent number: 11028705
    Abstract: A transition piece can include: an inner transition piece providing a gas channel; a plurality of cooling rings disposed on the inner transition piece; a plurality of film holes formed on the inner transition piece; and a plurality of impingement holes formed on the plurality of cooling rings, wherein the plurality of film holes are arranged to correspond to the plurality of cooling rings. Each of the plurality of cooling rings includes a cavity such that the plurality of film holes connect the cavity to the gas channel and the plurality of impingement holes connect the cavity to an outside of the inner transition piece.
    Type: Grant
    Filed: March 16, 2018
    Date of Patent: June 8, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd.
    Inventors: Esam Abu-Irshaid, Michael Brody, Kevin James Spence
  • Patent number: 11022304
    Abstract: A combustor is provided with a combustion liner (12) in which a combustion gas flows through the inner peripheral side and a plurality of through-holes (14) are formed, and a sound attenuator (20) having a space-forming member (21) configured to form a space (S) connected to the plurality of through-holes (14) at the outer peripheral side of the combustion liner (12). The space-forming member has a main body having an opening configured to bring an outside and the space in communication with each other, and a lid joined to an outer surface of the main body via a welded portion and configured to protrude outward and close the opening.
    Type: Grant
    Filed: January 27, 2020
    Date of Patent: June 1, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kenta Taniguchi, Kuniomi Hirano, Shin Kato, Yoshikazu Matsumura, Shingo Sato
  • Patent number: 10954834
    Abstract: Systems and methods for an exhaust system for a gas turbine engine are provided. The method includes: receiving a primary exhaust fluid in a primary manifold; receiving a secondary cooling fluid in a secondary plenum; directing the primary exhaust fluid through a plurality of eductor primary flow paths associated with a respective plurality of ducts spaced circumferentially about a primary manifold, the plurality of eductor primary flow paths extending through the secondary plenum; and mixing the primary exhaust fluid and the secondary cooling fluid in a mixing chamber associated with a respective one of the plurality of ducts to create a mixed fluid flow.
    Type: Grant
    Filed: August 7, 2018
    Date of Patent: March 23, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Yoonshik Shin, Yogendra Yogi Sheoran, Daniel Brown
  • Patent number: 10934937
    Abstract: A cooling system for an aircraft has at least one moveable member configured to cover an opening formed within an aircraft outer skin. An actuator moves the at least one moveable member between a fully open position where external atmosphere air can be directed through the opening to an internal passage enclosed by the aircraft outer skin and a fully closed position where the opening is covered. A controller selectively controls the actuator to move the at least one moveable member between the fully open and fully closed positions. An aircraft engine and a method of cooling an aircraft engine in an aircraft are also disclosed.
    Type: Grant
    Filed: July 19, 2016
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Pellegrino J. Pisacreta
  • Patent number: 10837368
    Abstract: An acoustic liner can comprise a support layer including a set of partitioned cavities defining a set of cells with open faces, as well as a first and second facing sheet operably coupled to the support layer that overlie and close the open faces. A set of aerogel fillings can be provided within at least some of the set of cells.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: November 17, 2020
    Assignee: MRA SYSTEMS, LLC
    Inventors: Graham Frank Howarth, David Patrick Calder, Andrew Michael Roach
  • Patent number: 10836503
    Abstract: An aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: November 17, 2020
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Alain Porte, Eric Haramburu, Patrick Oberle, Grégory Albet, Vincent Billerot, Frédéric Piard, Franck Oundjian
  • Patent number: 10731511
    Abstract: A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.
    Type: Grant
    Filed: February 22, 2013
    Date of Patent: August 4, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Robertson, Jr., Sreenivasa R. Voleti, Mark W. Costa, Steven Clarkson
  • Patent number: 10723476
    Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.
    Type: Grant
    Filed: November 9, 2018
    Date of Patent: July 28, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Cedric Zaccardi, Christophe Marcel Lucien Perdrigeon, Francois Marie Paul Marlin, Thierry Georges Paul Papin, Jacky Novi Mardjono
  • Patent number: 10662839
    Abstract: An exhaust stack assembly includes an exhaust stack having an internal surface that defines an interior of the exhaust stack. The exhaust stack is configured to receive exhaust gas from at least one turbomachine component and exhaust the exhaust gas to atmosphere. The exhaust gas assembly further includes a plurality of attenuation assemblies disposed in the interior, each of the plurality of attenuation assemblies including a base substrate generally oriented in the direction of flow of the exhaust gas through the interior, each of the plurality of attenuation assemblies further including a plurality of attenuation modules mounted to the base substrate. Each of the plurality of attenuation modules includes a fiber mesh. The fiber mesh is exposed to the exhaust gas in the interior.
    Type: Grant
    Filed: June 28, 2017
    Date of Patent: May 26, 2020
    Assignee: General Electric Company
    Inventors: Bradly Aaron Kippel, Matthew Alan Johnsen, Richard Lynn Loud
  • Patent number: 10662895
    Abstract: A fan nacelle for an aircraft gas turbine engine. The nacelle includes an aft nacelle portion including a radially outer surface and a radially inner surface, the radially outer and inner surfaces defining an internal cavity therebetween. The nacelle further includes an aft nacelle segment translatable along a translation vector having an axial component, wherein the aft nacelle segment is configured to translate between a forward deployed position in which the nacelle defines a first primary fan nozzle exit area (A1) and a clean position in which the nacelle defines a second primary fan nozzle exit area (A2) less than the first primary fan nozzle exit area A1, wherein in the forward deployed position, the aft nacelle segment is at least partly located within the internal cavity.
    Type: Grant
    Filed: May 12, 2017
    Date of Patent: May 26, 2020
    Assignee: ROLLS -ROYCE PLC
    Inventor: John R Wells
  • Patent number: 10641118
    Abstract: A sealing apparatus includes a sealing portion configured to be positioned between a platform of a turbine blade and an inner shroud of a turbine vane of a turbine, and an acoustic damper having a closed space portion which is configured to communicate, via an opening, with a disc cavity configured to be positioned between the turbine blade and the turbine vane.
    Type: Grant
    Filed: December 22, 2015
    Date of Patent: May 5, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kazufumi Ikeda, Hitoshi Kitagawa, Masato Araki, Yoshiyuki Okabe
  • Patent number: 10626886
    Abstract: A sound attenuation apparatus includes a body and a stacked cavity structure. The structure includes a structure inlet formed in the top surface of the body; a passage extending from the structure inlet into the interior of the body to a base surface within the body; a first cavity with a first cavity inlet fluidly coupled to the passage and being formed by a first arm, a first side wall within the interior of the body, and the base surface; and a second cavity with a second cavity inlet fluidly coupled to the passage and being formed by a second arm, the first side wall, and the first arm. Each of the first and second arms extends from the first side wall and includes at least two arm segments oriented at different angles relative to the first side wall longitudinal axis.
    Type: Grant
    Filed: April 18, 2018
    Date of Patent: April 21, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Mark McNair, William Schuster, Donald G. Godfrey
  • Patent number: 10626799
    Abstract: Acoustic structures in which acoustic septa are located in the cells of a honeycomb for reducing the noise generated from a source. The honeycomb used to form the acoustic structure has walls that contain convex and concave contours which make the honeycomb flexible. The acoustic septa are formed by inserting planar acoustic inserts into the honeycomb cells to form a septum cap which is friction-locked within the cell and then permanently bonded in place. The planar acoustic septum is configured to match the unique shape of the cell contours to provide desired friction-locking when inserted into the cells and desired acoustic properties after being permanently bonded in place.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: April 21, 2020
    Assignee: HEXCEL CORPORATION
    Inventors: Lisa D. Bowen, Jessica Miller
  • Patent number: 10619596
    Abstract: An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: April 14, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Guy Lefebvre, Patrick L'Esperance, Gabriel Emard-Parent
  • Patent number: 10578115
    Abstract: A composite component comprising fibres embedded in a matrix material. A plurality of pins extend through the matrix material. Each pin of the plurality of pins comprises a hollow bore such that the bore of each pin defines a plurality of holes in the composite component.
    Type: Grant
    Filed: April 25, 2017
    Date of Patent: March 3, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: James K Lander, Robert C Backhouse
  • Patent number: 10570852
    Abstract: An exhaust section of a gas turbine engine includes an exhaust plug defining a plurality of exhaust plug apertures circumferentially spaced from each other. Also included is an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. Further included is an exhaust plug liner having a non-uniform outer surface axially aligned with the exhaust plug apertures. The exhaust plug liner is rotatable relative to the exhaust plug between a first position and a second position to selectively change a cross-sectional area of the exhaust pathway during thrust reversal operation to reduce an amount of reverse thrust necessary.
    Type: Grant
    Filed: September 21, 2017
    Date of Patent: February 25, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Andre L. Bent, Steven H. Zysman, Nigel David Sawyers-Abbott
  • Patent number: 10480451
    Abstract: Methods and systems for restricting movement in a flow mixer including a plurality of lobes that each includes a trough, using a stiffener mechanism, are provided. The stiffener mechanism includes a first end portion configured to be coupled to a first lobe of the plurality of lobes and a second end portion configured to be coupled to a second lobe of the plurality of lobes. The stiffener mechanism also includes a body portion coupled between the first end portion and the second end portion such that the body portion is configured to restrict movement of the first and second lobes.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: November 19, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Thomas Richardson Pinney, Michael Best, Jonathan D. Embler, William P. Keith, Aristidis Sidiropoulos, Edward T. Tong
  • Patent number: 10473328
    Abstract: An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include resonator chambers (26) that may be welded in place within resonator chamber (26) receivers (24) but easily replaceable without exposing the resonator housing (18) to damage. In another embodiment, an inner surface (32) of the resonator chamber (26) may be offset radially outward from an inner surface (34) of the resonator housing (18), thereby creating a flow-path discontinuity and reducing heating of the resonator chamber (26).
    Type: Grant
    Filed: September 9, 2014
    Date of Patent: November 12, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventors: Reinhard Schilp, David M. Ritland, Erick J. Deane, Jaishree Sharma, Joseph Scott Markovitz
  • Patent number: 10385778
    Abstract: A system includes a silencer baffle which mounts in a fluid conduit along a fluid flow path, where the silencer baffle includes a plurality of baffle sections. At least two baffle sections of the plurality of baffle sections couple together via mating interlock structures, and at least one baffle section of the plurality of baffle sections has first and second baffle portions which couple together via mating joints.
    Type: Grant
    Filed: March 3, 2017
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: Hua Zhang, Jianhua Wang, Yanyan Liu, Naveen Ghattadhahalli Parmeshwar, Valery Ivanovich Ponyavin, Bradly Aaron Kippel
  • Patent number: 10371173
    Abstract: A gas turbine engine is provided having a fan case and a translating sleeve positioned downstream from the fan case. A flow channel extends between the fan case and the translating sleeve. The flow channel includes an inner diameter and an outer diameter. A structural guide vane is positioned within the flow channel and extends from the inner diameter to the outer diameter. A liner is positioned between an aft end of the fan case and an aft end of the translating sleeve to reduce vibratory stress on the structural guide vane.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Michaela M. Logue, Oliver V. Atassi
  • Patent number: 10371001
    Abstract: A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan. A nozzle associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.
    Type: Grant
    Filed: January 28, 2016
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Constantine Baltas, Amr Ali
  • Patent number: 10302017
    Abstract: A method of making a light weight component is provided. The method including the steps of: forming a metallic foam core into a desired configuration; applying an external metallic shell to an exterior surface of the metallic foam core after it has been formed into the desired configuration; and attenuating the component to a desired frequency by forming a plurality of openings in the external metallic shell.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: May 28, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 10228138
    Abstract: A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor inner liner. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is greater than or equal to the axial dimension.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: Andre Theuer, Dariusz Oliwiusz Palys, Jost Imfeld, Bruno Schuermans
  • Patent number: 10221769
    Abstract: A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one extended resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one extended resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is less than the axial dimension.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: March 5, 2019
    Assignee: General Electric Company
    Inventors: Jost Imfeld, Andre Theuer, Bruno Schuermans, Naresh Kumar Aluri
  • Patent number: 10190536
    Abstract: A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.
    Type: Grant
    Filed: September 17, 2012
    Date of Patent: January 29, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Patent number: 10125684
    Abstract: A gas turbine engine has a surface cooler having a cooler member defining a fluid passage and at least partially contained in an airfoil shaped flow guide member. The cooler member is disposed within a bypass duct and supported on one of the duct walls. The flow guide member provides a smooth outer surface to guide a main portion of a bypass air stream passing over the surface cooler, and defines an inner air channel between the flow guide member and that supporting one of the duct walls for a secondary portion of the bypass air stream to pass through the inner air channel.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: November 13, 2018
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Hong Yu
  • Patent number: 10087824
    Abstract: A turbocharger turbine having housing walls defining a diffuser. Within the diffuser, a center body within the diffuser is supported by de-swirl vanes extending from the diffuser wall. The center body forms a de-swirl passageway having an increasing mean diameter of flow from an upstream end of the center body to a leading edge of the de-swirl vanes. A trailing edge of the de-swirl vanes is near the downstream end of the center body. Annular-type guide vanes surround the center body within the de-swirl passageway. A wastegate system is configured to vent wastegate flow into the diffuser through injection ports on the de-swirl vanes, annular guide vanes and/or center body.
    Type: Grant
    Filed: February 25, 2015
    Date of Patent: October 2, 2018
    Assignee: GARRETT TRANSPORTATION 1 INC.
    Inventors: Christopher W. Wilkins, Wagner M. Magalhaes, Bharathi Raja Sugumaran, Martin Babak
  • Patent number: 10036327
    Abstract: The invention relates to a damper for reducing the pulsations in a chamber of a gas turbine. The damper includes a resonator cavity and a neck in flow communication with the resonator cavity and the chamber. The neck includes a mouth to communicate with the chamber. The air flow inside the chamber flows across the mouth of the neck. The neck is so configured that the longitudinal axis of its mouth is angled 0-90° relative to the direction of the air flow inside the chamber. The damper of this invention may effectively alleviate the detrimental effect of the grazing flow and thus it enables the placement of the damper also at locations where strong grazing flows are present.
    Type: Grant
    Filed: October 24, 2014
    Date of Patent: July 31, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Devis Tonon, Mirko Ruben Bothien, Franklin Marie Genin, Douglas Anthony Pennell
  • Patent number: 10018071
    Abstract: In one embodiment, a turbine system includes a number of sensors, each of the number of sensors disposed in a respective location of the turbine system, and a controller including a memory storing one or more processor-executable routines and a processor. The processor configured to access and execute the one or more routines encoded by the memory wherein the one or more routines, when executed cause the processor to receive one or more signals from the number of sensors during any stage of operation of the turbine system, and convert the one or more signals to audio output.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: July 10, 2018
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Paige Marie Sopcic, Jason Dean Fuller, Daniel Joseph Flavin
  • Patent number: 10018088
    Abstract: A Helmholtz damper for a combustor of a gas turbine includes an enclosure defining a damping volume from which a neck portion extends and which has a flow path (F) for cooling and purging air with an inlet opening and an outlet opening to the enclosure. The outlet opening is formed in the neck portion. A seal is arranged at the neck portion adjacent to the outlet opening for cooling and purging air such that a cooling effect of the seal is provided.
    Type: Grant
    Filed: October 9, 2014
    Date of Patent: July 10, 2018
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventor: Adnan Eroglu
  • Patent number: 9997977
    Abstract: A dual engine generator has two engines and two inverters and two alternators configured within an inner enclosure. An outer enclosure extends around the inner enclosure to create plenums for airflow. Cooling airflow enters through the outer cover and flows through the plenums and into the inner enclosure to cool the components therein. Airflows out of the inner enclosure and into the plenums and finally exhausts from the outer enclosure. The outer enclosure may have rounded sides to form a pill shaped enclosure. The outer covers are configured to deflect or flex in high wind condition and protect the inner enclosure. The engines are configured above the alternator and inverter and a flow of air reduces heat from the engines from overheating the other components. The mufflers are within the plenums and a flow of exhaust air from within the inner enclosure is directed over the mufflers.
    Type: Grant
    Filed: February 21, 2017
    Date of Patent: June 12, 2018
    Assignee: MWE Investments LLC
    Inventor: Michael John Roll
  • Patent number: 9964070
    Abstract: A gas turbine engine exhaust nozzle comprises a housing having an aft end that terminates in a row of chevrons. At least one surface of the housing has scalloped root regions proximate bases of adjacent chevrons. The scalloped root regions have a reduced thickness relative to the rest of the aft end.
    Type: Grant
    Filed: January 21, 2013
    Date of Patent: May 8, 2018
    Assignee: The Boeing Company
    Inventors: David F. Cerra, Lie-Mine Gea, Robert H. Willie, Leonard J. Hebert, Donald E. Robinson
  • Patent number: 9919786
    Abstract: The present invention relates to acoustical panels. As to provide a cabin panel to be made as simple as possible and with optimized acoustical properties, an acoustical cabin panel (10) is provided that comprises a first (12) and a second layer (14) which are spaced apart from each other by an intermediate layer (16) and altogether with a plurality of reinforcement elements (22) form a core composite component (24). Furthermore, the panel comprises at least one intermediate layer (18) made of a core material (20) which is arranged in the intermediate layer. The reinforcement elements extend from the first to the second layer through the at least one intermediate film and are tension and pressure resilient in a finished state of the panel. The reinforcement elements can be at least partially infiltrated with a curable matrix material and at least one prepreg (26) soaked with matrix material is provided in the first and/or second layer.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: March 20, 2018
    Assignees: AIRBUS DEFENCE AND SPACE GMBH, AIRBUS OPERATIONS GMBH
    Inventors: Christian Gregor Endres, Hans-Jürgen Weber
  • Patent number: 9896970
    Abstract: A method and system for a compartment baffle system are provided. The compartment baffle system includes a first baffle portion extending along an axial length of a casing, the first baffle portion extending radially outwardly from an outer surface of the casing and a second baffle portion extending at least partially radially outwardly from the first baffle portion. The second baffle portion further includes a radially inner edge supported by the first baffle portion and a radially outer edge extending proximate an inner surface of a radially outer cowl. The compartment baffle system also includes a gap extending between the radially outer edge and the inner surface.
    Type: Grant
    Filed: October 30, 2015
    Date of Patent: February 20, 2018
    Assignee: General Electric Company
    Inventors: Kyle Andrew Grose, Arjan Johannes Hegeman, Andrew David Kemp, John Michael Pyles
  • Patent number: 9884688
    Abstract: A propulsion system for a supersonic aircraft includes an engine including an engine core and an engine bypass, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a plurality of vortex generators positioned upstream of the engine. The vortex generators have a height such that when the supersonic aircraft is flown at a predetermined altitude and predetermined speed, the plurality of vortex generators create vortices that propagate partially outside of a boundary layer formed proximate a surface of a supersonic inlet. The vortices cause a high-velocity portion of the airflow to move towards the engine core and a low-velocity portion of the airflow to move towards the engine bypass. The plurality of vortex generators are disposed aft of a terminal shock and have a height greater than the thickness of the boundary layer.
    Type: Grant
    Filed: February 4, 2014
    Date of Patent: February 6, 2018
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Michael Rybalko, Timothy R. Conners, Thomas R. Wayman
  • Patent number: 9816440
    Abstract: In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: November 14, 2017
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Takanori Ito, Keisuke Matsuyama, Kazufumi Ikeda, Satoshi Tanimura, Shinji Akamatsu
  • Patent number: 9783316
    Abstract: An acoustic panel structure includes a perforated front sheet, a back sheet and a porous core between the front sheet and the back sheet. The acoustic panel structure also includes a non-perforated back cover which overlaps a portion of the back sheet. A portion of the back sheet is perforated and another portion of the back sheet is not perforated. An acoustic chamber is formed at least in part by the space between the back sheet and the back cover. The acoustic chamber may also be formed in part by the space between the front sheet and back cover. The space between the back sheet and the back cover is generally elongated in the x-y direction of the acoustic panel structure. This relatively thin acoustic panel structure is configured to attenuate long wavelength and low frequency noise.
    Type: Grant
    Filed: June 22, 2015
    Date of Patent: October 10, 2017
    Assignee: Rohr, Inc.
    Inventor: Jose S. Alonso-Miralles
  • Patent number: 9784247
    Abstract: An apparatus for dampening of acoustic noise generated by air-cooling of at least one turbine component provided with the nacelle of a wind turbine is provided. Apparatus for dampening of acoustic noise generated by air-cooling of at least one wind turbine component provided with the nacelle of a wind turbine, comprising at least one acoustic dampener, with the acoustic dampener including at least one acoustic dampening channel structure having at least one acoustic dampening channel connected with at least one inlet opening of the acoustic dampening channel structure and at least one outlet opening of the acoustic dampening channel structure.
    Type: Grant
    Filed: March 10, 2015
    Date of Patent: October 10, 2017
    Assignee: Siemens Aktiengesellschaft
    Inventors: Uffe Eriksen, Steffen Lorentzen, Thorkil Munk-Hansen, Claus Thygesen
  • Patent number: 9708072
    Abstract: An engine nacelle includes an exterior wall and an interior wall. A forward bulkhead is coupled between the interior wall and the exterior wall, wherein the forward bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall. The engine nacelle also includes an aft bulkhead coupled between the interior wall and the exterior wall, wherein the aft bulkhead comprises a curvilinear body portion that extends between the interior wall and the exterior wall.
    Type: Grant
    Filed: April 30, 2014
    Date of Patent: July 18, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Alex C. Lumbab, Bradley Scott Leisten
  • Patent number: 9663239
    Abstract: An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser directs thrust at an angle relative to a vertical plane to reduce interference on control surfaces and reduce generation of underbody lift.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: May 30, 2017
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler
  • Patent number: 9663238
    Abstract: A nacelle inlet is provided for a turbo-fan engine for an aircraft. The nacelle inlet includes a lip skin having first and second pad-ups, an inner barrel including a forward flange and a bulkhead. The bulkhead, the lip skin and the inner barrel are attached together at mating surfaces. The bulkhead and the lip skin are attached together at mating surfaces. Each mating surface defines a surface geometry which approximates a developable surface having parallel ruling lines. The developable surfaces are formed by machining.
    Type: Grant
    Filed: November 11, 2013
    Date of Patent: May 30, 2017
    Assignee: The Boeing Company
    Inventors: Daniel J. Kane, Stuart W. Vogel, Hoa V. Truong, Michael W. Kass, Andrew T. Gilmore, Paul D. Whitmore, Jack W. Mauldin, Alejandro Silva, John Ybarra
  • Patent number: 9657644
    Abstract: A method for mounting an acoustic panel on the inner surface of an annular housing of an axial turbomachine, the cylindrical acoustic panel comprising at least one longitudinal slot so as to define two opposing ends, the method comprising: bringing the two opposing ends closer together so as to reduce the cylinder radius of the acoustic panel; inserting the acoustic panel into the fan casing when the opposing ends are close together; deploying the opposing ends so as to increase the cylinder radius of the acoustic panel; and securing the acoustic panel to the housing by gluing.
    Type: Grant
    Filed: September 11, 2013
    Date of Patent: May 23, 2017
    Assignee: SNECMA
    Inventors: François Sfarti, François Marie Paul Marlin
  • Patent number: 9640164
    Abstract: A method and apparatus for attenuating sound. Air, through which acoustic waves are traveling, is received within a core comprised of a plurality of cells. The sound created by the acoustic waves is attenuated using a set of channels through a number of cell interfaces between cells of the plurality of cells by allowing the air to flow between the cells of the plurality of cells through the set of channels.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: May 2, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Noel Timothy Gerken, Eric Herrera, Garry Michael Duschl
  • Patent number: 9631640
    Abstract: An acoustic protection device for a fan casing of an aircraft turbomachine, including an acoustic protection panel forming a ferrule sector centered on a center axis, and one or more vibration damping strips pressed on a first side to an external surface of the panel and on a second side to an internal surface of the casing, each damping strip including two opposite edges each including an upstream end and a downstream end spaced from each other along a direction of the center axis. At least one of both opposite edges of at least one of the damping strips is shaped such that liquid present on this edge can flow by gravity towards either or both of its upstream and downstream ends.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: April 25, 2017
    Assignee: SNECMA
    Inventors: Guillaume Roffi, Julien Tran
  • Patent number: 9587632
    Abstract: A thermally-controlled component and thermal control process are disclosed. The thermally-controlled component includes thermally-responsive features. The thermally-responsive features are configured to modify a flow path to control temperature variation of the thermally-controlled component. The thermally-responsive features deploy from or retract toward a surface of the thermally-controlled component in response to a predetermined temperature change. The thermal control process includes modifying the flow path in the thermally-controlled component to control temperature variation of the thermally-controlled component and/or cooling a region of the thermally-controlled component through the thermally-responsive features deploying from or retracting toward a surface of the thermally-controlled component.
    Type: Grant
    Filed: November 30, 2012
    Date of Patent: March 7, 2017
    Assignee: General Electric Company
    Inventors: Paul Stephen Dimascio, Michael Douglas Arnett, Rebecca Evelyn Hefner
  • Patent number: 9540114
    Abstract: An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.
    Type: Grant
    Filed: March 3, 2014
    Date of Patent: January 10, 2017
    Assignee: United Technologies Corporation
    Inventors: Eric Andrew Nager, James C. Napier, Farooq Rehman, Anthony C. Jones
  • Patent number: 9355194
    Abstract: An interactive liner design and impedance modeling tool comprises software utilized to design acoustic liners for use in constrained spaces, both regularly and irregularly shaped. A graphical user interface allows the acoustic channel geometry to be drawn in a liner volume while the surface impedance calculations are updated and displayed in real-time. A one-dimensional transmission line model may be used as the basis for the impedance calculations.
    Type: Grant
    Filed: February 20, 2013
    Date of Patent: May 31, 2016
    Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
    Inventors: Brian M. Howerton, Michael G. Jones
  • Patent number: 9334059
    Abstract: An acoustic panel liner includes a face sheet, back plate, and liner core positioned therebetween, which may be used in an engine nacelle. Elongated chambers contain variable amounts of septa at a calibrated depth or depths. The septa may have varying DC flow resistance. The chambers may have a hexagonal or other polygonal cross sections. The septa, such as mesh caps, may be bonded to an inner wall of a corresponding chamber. The insertion depths may be the same or different. If different, the pattern of distribution of the depths may be randomized.
    Type: Grant
    Filed: June 5, 2014
    Date of Patent: May 10, 2016
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Michael G. Jones, Douglas M. Nark, Earl Ayle, Fumitaka Ichihashi
  • Patent number: 9200537
    Abstract: A turbine exhaust case for a gas turbine engine has an outer shroud and an inner shroud concentrically defining therebetween an annular gaspath for channelling hot gases. A plurality of circumferentially spaced-apart turbine exhaust struts extends radially across the hot gaspath. The inner shroud may be provided in the form of an acoustic panel. The acoustic panel has a radially outwardly facing surface defining the radially inner flow boundary surface of the gaspath. The acoustic panel is mechanically fastened to the radially inner end of the struts.
    Type: Grant
    Filed: November 9, 2011
    Date of Patent: December 1, 2015
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Bouchard, Gaetan Girard, Christian Pronovost
  • Patent number: 9169804
    Abstract: A duct and a method for damping pressure waves caused by thermoacoustic instability, the duct comprising: a locking Helmholtz resonator positioned on the circumference of the duct, the locking Helmholtz resonator tuned to a first frequency; and one or more damping Helmholtz resonators positioned on the circumference of the duct at or adjacent to 90 and/or 270 degrees from the locking Helmholtz resonator, wherein the damping Helmholtz resonators are tuned to a second frequency which is different from the first frequency of the locking Helmholtz resonator.
    Type: Grant
    Filed: June 25, 2014
    Date of Patent: October 27, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Jochen Rupp, Anthony John Moran