Patents Examined by Kyle Thomas
  • Patent number: 10378483
    Abstract: A motor assembly is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber.
    Type: Grant
    Filed: November 12, 2015
    Date of Patent: August 13, 2019
    Assignee: Raytheon Company
    Inventors: James Kendall Villarreal, Mark T. Langhenry, Jeremy C. Danforth
  • Patent number: 10309346
    Abstract: A cylindrically-shaped hybrid rocket engine solid fuel grain defines an axial combustion port. A fuel grain material comprises a compounded blend of thermoplastic fuel and aluminum. The fuel grain comprises fused stack layers, each layer comprising a plurality of fused abutting concentric beaded structures arrayed to define the combustion port; the port exhibits a rifling pattern or rifling inducing geometry along the port wall. When an oxidizer is introduced into the combustion port combustion occurs along the exposed port wall. Each beaded structure defines a geometry that increases the combustion surface area while inducing a vortex flow of oxidizer and fuel gas. As each layer ablates, an abutting layer exhibiting a similar geometry, is revealed, undergoes a gas phase change, and ablates. This process repeats and persists until oxidizer flow is terminated or the fuel grain material is exhausted. The fuel grain may be manufactured by an additive manufacturing process.
    Type: Grant
    Filed: January 11, 2018
    Date of Patent: June 4, 2019
    Inventor: Ronald D Jones
  • Patent number: 10273821
    Abstract: In one aspect, the present subject matter is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a first seal layer defining a first seal layer aperture extending therethrough. A second seal layer defines an elongated slot extending therethrough. The elongated slot includes a first end and a second end. A third seal layer defines a third seal layer aperture extending therethrough. The second seal layer is positioned between the first seal layer and the third seal layer such that the first seal layer aperture is in fluid communication with the first end and the third seal layer aperture is in fluid communication with the second end.
    Type: Grant
    Filed: September 10, 2015
    Date of Patent: April 30, 2019
    Assignee: General Electric Company
    Inventor: Dylan James Fitzpatrick
  • Patent number: 10132175
    Abstract: An arrangement (10) for delivering gases from combustors (15) to a first row of blades. The arrangement (10) includes at least an upstream flow path (60) including an aft first side wall (64) and a downstream flow path (62) including a forward second side wall (66). A convergence junction trailing edge (40) is defined at a downstream terminal edge (41) of the first side wall (64), and the second side wall (66) converges toward the first side wall (64) in the direction of the convergence junction trailing edge (40). An impingement sheet structure (78) is located between and provides impingement cooling air to the first and second side walls (64, 66). Openings (88) provide a cooling air passage between the first and second side walls (64, 66) and provide a flow of post impingement air into the gas path at the convergence junction trailing edge (40).
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: November 20, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventor: David A. Little
  • Patent number: 10132197
    Abstract: Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.
    Type: Grant
    Filed: April 20, 2015
    Date of Patent: November 20, 2018
    Assignee: General Electric Company
    Inventors: Bryce Loring Heitman, Michael Todd Radwanski, Darrell Glenn Senile
  • Patent number: 10107196
    Abstract: An adjustable size inlet duct system for a ducted fan propulsion system may change its inlet profile to enhance thrust levels in low-speed and hovering flight conditions and may change its inlet profile to reduce drag to permit faster flight speeds at higher operating speeds. The adjustable size inlet duct system may include duct petals and associated actuators. During slow speed flight, the petals may expand to generate a rounded large inlet area bellmouth profile. At higher flight speeds, the petals may contract to reduce the profile drag of the duct in forward flight. An optional exterior bypass duct may be included to provide additional thrust in excess of the thrust provided by the ducted fan. An optional annular electric motor housed in the exterior bypass duct may be included to generate still more excess thrust.
    Type: Grant
    Filed: August 8, 2014
    Date of Patent: October 23, 2018
    Assignee: Thomas International, Inc.
    Inventor: Michael Thomas Devine
  • Patent number: 10101032
    Abstract: A micromixer system includes a casing having a first side wall and a second side wall. Further, the micromixer system includes a plurality of pipes spaced apart from each other and disposed within the casing. Each pipe includes an inlet and an outlet formed in the first and second side walls respectively. The micromixer system includes a first plenum having a first inlet formed in the casing. The first plenum is disposed around a first portion of the plurality of pipes and fluidically coupled to the plurality of pipes. The micromixer system includes a second plenum having a second inlet formed in the casing and disposed around a second portion of the plurality of pipes. Further, the micromixer system includes a plurality of openings formed in the second side wall, surrounding the outlets of at least some pipes of the plurality of pipes, and fluidically coupled to the second plenum.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: October 16, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Bassam Sabry Mohammad Abd El-Nabi, Gregory Allen Boardman, Gerardo Antonio Salazar Lois
  • Patent number: 10094277
    Abstract: A method for assembling and disassembling a module of gas turbine engine is provided, along with a gas turbine engine configured for modular assembly/disassembly. The engine includes a first shaft and a second shaft. The first shaft connects a compressor section and a first turbine section. The second shaft is connected to the second turbine section. The first and second shafts are rotatable about the engine rotational axis. The second shaft and the second turbine section together form a module that can be assembled, or disassembled, or both from the engine.
    Type: Grant
    Filed: June 19, 2015
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventor: Paul R. Hanrahan
  • Patent number: 10082040
    Abstract: The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: September 25, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Francois Gallet, Nicolas Jerome Jean Tantot
  • Patent number: 10072584
    Abstract: A gas turbine engine comprises a first bypass flow path housing configured within the engine, radially exterior to an engine core housing, and a second bypass flow path housing configured within the engine, radially exterior to the first bypass flow path housing. An axially downstream portion of the first bypass flow path housing includes a stepwise increase in area compared with an axially adjacent upstream portion of the first bypass flow path housing, thereby defining a component placement cavity in the axially downstream portion.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: September 11, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael R. Thomas, Nathan Snape
  • Patent number: 10030606
    Abstract: A gas turbine engine includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is included inboard of the outer case structure. An inner case structure is included inboard of the intermediate case structure. A variable area exhaust mixer is included, which is movable between a closed position adjacent to the intermediate case structure and an open position adjacent to the inner case structure.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: July 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Francis R. Moon, Daniel B. Kupratis
  • Patent number: 10024197
    Abstract: A power generation system may include a generator, and a gas turbine system for powering the generator, the gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A turbo-expander may also power the generator. A first control valve control flow of the excess air flow along an excess air flow path to an inlet of the turbo-expander. An educator may be positioned in the excess air flow path for using the excess air flow as a motive force to augment the excess air flow with additional air. A discharge of the turbo-expander is supplied to an inlet of the integral compressor.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: July 17, 2018
    Assignee: General Electric Company
    Inventors: Sanji Ekanayake, Kihyung Kim, Alston Ilford Scipio, Leslie Yung Min Tong, Michael Wesley Yarnold
  • Patent number: 10001136
    Abstract: A gas turbine engine exhaust panel mounting system comprising a panel, a casing and an attachment assembly for removably connecting the panel to the casing comprises a retaining portion, a clamping portion, and a ā€˜Cā€™-shaped connecting link. The connecting link has a first attachment portion and an opposite second attachment portion with the first and second attachment portions being connected to one another by a center portion. Each of the first and second attachment portions is substantially parallel to one another and extends in the same direction from respective ends of the center portion. The first attachment portion is fixedly connected to the casing by the clamping portion, and the second attachment portion is slidingly connected to the panel by the retaining portion.
    Type: Grant
    Filed: July 16, 2014
    Date of Patent: June 19, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Paul Robert Hayton
  • Patent number: 10001281
    Abstract: A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis and having an exterior surface, and having a ring of forward openings passing through the exterior surface, and a ring of aft openings passing through the exterior surface, the aft openings positioned axially aft of the forward openings; an annular main injection ring disposed inside the outer body and including: a forward main fuel gallery extending in a circumferential direction; an aft main fuel gallery extending in a circumferential direction; a ring of forward main fuel orifices communicating with the forward main fuel gallery and each aligned with one of the forward openings; a ring of aft main fuel orifices, communicating with the aft main fuel gallery and each aligned with one of the aft openings; and a pilot fuel injector disposed along the centerline axis.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: June 19, 2018
    Assignee: General Electric Company
    Inventors: Nayan Vinodbhai Patel, Duane Douglas Thomsen
  • Patent number: 9995222
    Abstract: A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: June 12, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Matthew P. Forcier
  • Patent number: 9989256
    Abstract: An injection system for a turbine engine combustion chamber is provided. The injection system includes a first annular deflector surrounded by the bowl of the injection system and extending in the downstream direction from the downstream transverse surface that delimits the downstream side of the swirler. The first deflector has a free downstream end offset in the upstream direction from a downstream end of the bowl, so as to guide an air film output from the first orifices formed through the bowl. The internal radius of the cross section of the first annular deflector increases from the downstream transverse surface as far as the downstream end of the first annular deflector.
    Type: Grant
    Filed: June 25, 2015
    Date of Patent: June 5, 2018
    Assignee: SNECMA
    Inventors: Denis Jean Maurice Sandelis, Romain Nicolas Lunel
  • Patent number: 9964114
    Abstract: A noise attenuation panel for a bleed flow is presented that causes a total pressure loss of the bleed flow before it is exhausted. The total pressure loss results from at least two regions in which the flow area contracts and then rapidly expands, with the rapid expansion causing mixing and turbulence rather than full total pressure recovery. This reduced pressure means that when the flow is exhausted into a flow (which may be the bypass flow of a gas turbine engine), its energy, and thus its noise, are reduced.
    Type: Grant
    Filed: December 8, 2014
    Date of Patent: May 8, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Oliver C Taylor-Tibbott
  • Patent number: 9951693
    Abstract: A fuel supply system for a gas turbine combustor includes a fuel distribution manifold. A first fuel circuit extends from the fuel distribution manifold in a first circumferential direction around an outer surface of the outer casing and provides for fluid communication from the fuel distribution manifold, through the outer casing and to at least one fuel injector disposed within the outer casing. A second fuel circuit extends from the fuel distribution manifold in a second circumferential direction around the outer surface of the outer casing. The second fuel circuit provides for fluid communication from the fuel distribution manifold, through the outer casing and to at least one fuel injector within the outer casing. In particular configurations, the fuel supply system includes a shield that surrounds at least a portion of the outer casing and at least partially encases the first fuel circuit and the second fuel circuit.
    Type: Grant
    Filed: February 24, 2015
    Date of Patent: April 24, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Nazar Ahmed Elwasila, Robert Joseph Rohrssen, Ronnie Ray Pentecost, Lucas John Stoia
  • Patent number: 9951954
    Abstract: A method of lining a turbofan casing (30) with an array (32) of liner modules (34), including the steps of: providing a liner module (34); and providing a coupling element (48) on the casing for interlocking engagement with the liner module to maintain the liner module in position relative to the casing; and interlockingly engaging the liner module (34) and coupling element (48) by progressive movement of the liner module relative to the coupling element.
    Type: Grant
    Filed: March 6, 2015
    Date of Patent: April 24, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Christopher Benson, Matthew Ashley Charles Hoyland
  • Patent number: 9945324
    Abstract: Aspects of the disclosure are directed to a system for a thrust reverser of an aircraft comprising: a primary sleeve, and a secondary sleeve, wherein a first stroke associated with the primary sleeve is different from a second stroke associated with the secondary sleeve, and wherein the primary sleeve traverses a first distance associated with the first stroke at the outset of a deployment of the thrust reverser and a second distance associated with the first stroke at a later stage of the deployment.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: April 17, 2018
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley