Patents Examined by Craig Kim
  • Patent number: 10184425
    Abstract: A control system for a variable area fan nozzle (VAFN) having a plurality of petals is disclosed. The control system may include at least one fiber optic shape sensor extending along at least one of the plurality of petals, and a light source operatively connected to the at least one fiber optic shape sensor. The control system may further include a receiver operatively connected to the at least one fiber optic shape sensor. The control system may further include a VAFN control unit in operative communication with the plurality of petals and the receiver. The VAFN control unit may be configured to receive a signal from the receiver indicative of the measured strain along the at least one fiber optic shape sensor, and calculate a nozzle area of the VAFN based on the measured strain.
    Type: Grant
    Filed: January 28, 2016
    Date of Patent: January 22, 2019
    Assignee: The Boeing Company
    Inventors: Jason J. Jackowski, Kent E. Karnofski
  • Patent number: 10184665
    Abstract: A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24° to about 40° in relation to a centerline axis.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: January 22, 2019
    Assignee: General Electric Company
    Inventors: Michael Anthony Benjamin, Alfred Albert Mancini, Rameshkumar Muthuvel Chandrasekaran
  • Patent number: 10184402
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.
    Type: Grant
    Filed: April 9, 2018
    Date of Patent: January 22, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry
  • Patent number: 10174949
    Abstract: A heat shield for a combustor of a gas turbine engine includes a first edge with a first set of cantilevered members and a second edge with a second set of cantilevered members.
    Type: Grant
    Filed: February 5, 2014
    Date of Patent: January 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Nurhak Erbas-Sen
  • Patent number: 10174763
    Abstract: A variable pitch fan assembly for an aero gas turbine engine that includes a row of fixed pitch blades in a core stream flow and a row of variable pitch blades in a bypass stream flow, and where a sync ring with a number of hydraulic actuators within a flow splitter of the fan stage is used to vary a pitch of each of the bypass stream flow blades. Hydraulic fluid lines pass through the shaft and through the fixed pitch fan blades into the hydraulic actuators to move the sync ring and vary a pitch of the variable pitch bypass flow fan blades.
    Type: Grant
    Filed: August 2, 2018
    Date of Patent: January 8, 2019
    Assignee: FLORIDA TURBINE TECHNOLOGIES, INC
    Inventors: John A Orosa, Robert A Ress, Jr.
  • Patent number: 10174682
    Abstract: Provided are more efficient techniques for operating gas turbine systems. In one embodiment a gas turbine system comprises an oxidant system, a fuel system, a control system, and a number of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. The gas turbine system also includes a number of oxidant-flow adjustment devices, each of which are operatively associated with one of the combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into the associated combustor. An exhaust sensor is in communication with the control system. The exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and the control system is configured to independently adjust each of the oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: January 8, 2019
    Assignee: ExxonMobil Upstream Research Company
    Inventors: Franklin F. Mittricker, Richard A. Huntington
  • Patent number: 10167778
    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.
    Type: Grant
    Filed: April 28, 2017
    Date of Patent: January 1, 2019
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Donald E. Army, Gregory L. DeFrancesco, John M. Maljanian
  • Patent number: 10151204
    Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: December 11, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Houston, Tracy A. Propheter-Hinckley, Benjamin T. Fisk, Anita L. Tracy
  • Patent number: 10145558
    Abstract: A method for determining the temperature of an aggressive and/or abrasive gas is described using an acoustic transmitter and an acoustic receiver. The transmitter emits an acoustic signal with varying frequencies and the receiver extracts from the acoustic input signal a frequency of the maximum. Based on this the frequency of this maximum the temperature of the gas between transmitter and receiver is calculated.
    Type: Grant
    Filed: September 25, 2014
    Date of Patent: December 4, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Bruno Schuermans, Dominik Wassmer
  • Patent number: 10145561
    Abstract: A bundled tube fuel nozzle assembly including a fuel plenum and an air plenum. A plurality of mixing tubes extend through the fuel plenum and the air plenum. At least one resonator is positioned in the air plenum surrounding at least one of the plurality of mixing tubes.
    Type: Grant
    Filed: September 6, 2016
    Date of Patent: December 4, 2018
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Donald Mark Bailey, Sven Georg Bethke, Mohan Krishna Bobba
  • Patent number: 10145336
    Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.
    Type: Grant
    Filed: October 24, 2014
    Date of Patent: December 4, 2018
    Assignee: United Technologies Corporation
    Inventors: John R. Buey, Robert H. Bush, Felix Izquierdo
  • Patent number: 10139109
    Abstract: Can-annular burners for gas turbine engines with flow conditioners having locally varying, asymmetrical patterns of circumferential perforations, to promote uniform fuel-air mixture among all premixers in the burner basket. Any one or more of the perforation pattern, pattern density, perforation profiles and perforation cross sectional area is locally varied to alter circumferential airflow into the burner basket, which in turn mitigates non-uniform thru-flow variations across the burner's air inlet plane. In some embodiments, the flow conditioner asymmetric perforation patterns are tailored for individual burner locations within the engine's combustor section annular ring, which mitigates non-uniform thru-flow variation among different respective burners in the combustor section annular ring. Thru-flow uniformity within each burner and among all the combustor section burners promotes uniform engine combustion.
    Type: Grant
    Filed: January 7, 2016
    Date of Patent: November 27, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard L. Thackway, Charalambos Polyzopoulos, James M. Hurney
  • Patent number: 10139108
    Abstract: A combustor basket assembly for a gas turbine engine that includes a combustor basket having a basket liner including an input end and an output end. An integrated exit cone and splash plate member is affixed to the output end of the basket liner and includes a base portion, an exit cone portion and a splash plate portion. The base portion includes an annular cooling channel that receives a cooling air flow and the exit cone portion and the splash plate portion each include an array of cooling feed holes in fluid communication with the cooling channel. The spacing between the feed holes and the size of the feed holes can be optimized to provide more cooling for hotter regions.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: November 27, 2018
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Richard L. Thackway, Charalambos Polyzopoulos, Jr., James M. Hurney
  • Patent number: 10132242
    Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.
    Type: Grant
    Filed: April 26, 2013
    Date of Patent: November 20, 2018
    Assignee: General Electric Company
    Inventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
  • Patent number: 10131010
    Abstract: A brazed end cover assembly for a gas turbine combustor using Au—Ni braze is disclosed. The end cover assembly may include an end cover with openings, a flow insert, first and second gaps between the end cover and the flow insert, and first and second braze joints formed at the first and second gaps, wherein the braze materials used comprises Au and Ni. A method of brazing a flow insert into an end cover is also disclosed. The method may include providing an end cover and a flow insert with first and second gaps therebetween; applying a braze material to an outer surface of the flow insert, wherein the braze material comprises Au and Ni; inserting the flow insert into the end cover; heating the assembly to a brazing temperature for some time; and cooling the resulting brazed assembly to room temperature.
    Type: Grant
    Filed: June 28, 2012
    Date of Patent: November 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Gary J Dillard
  • Patent number: 10132243
    Abstract: A mounting and dismounting device for a liner of a gas turbine includes two inner rails attached at the turbine housing and each one having a first straight portion, two straight outer rails releasably attached at the turbine housing, wherein the adjacent free ends of the inner and outer rails can be positioned in full alignment one to the other. The rails are adapted to support the liner to be moveable in its axial direction. The inner rails include a second straight portion connected to the first straight portion through a curved portion wherein the axis of the second straight portion is parallel to the axis of the combustion gas passageway.
    Type: Grant
    Filed: March 11, 2016
    Date of Patent: November 20, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Stephen Wilder Jorgensen, Joshua R. McNally, Heinz Gerber, Davide Aratori, Douglas Anthony Pennel, Daniel Seng
  • Patent number: 10113747
    Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: October 30, 2018
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Hasan Karim, Joel Meador Hall
  • Patent number: 10113559
    Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.
    Type: Grant
    Filed: September 10, 2015
    Date of Patent: October 30, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew A. Turner, Colin J. Kling, David A. Topol
  • Patent number: 10113484
    Abstract: A muffling device for exhausting at least one fluid flow in a gas turbine engine includes a first diffuser coupled in flow communication with a first conduit. The first diffuser is configured to exhaust a first fluid flow. The device further includes a second diffuser disposed adjacent the first diffuser. The second diffuser is coupled in flow communication with a second conduit. The second diffuser is configured to exhaust a second fluid flow. The device also includes a third diffuser at least partially surrounding the first diffuser and the second diffuser. The third diffuser is coupled in flow communication with the first diffuser and the second diffuser. The third diffuser includes a body with apertures and is configured to exhaust a third fluid flow. The third fluid flow includes at least one of the first fluid flow and the second fluid flow.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: October 30, 2018
    Assignee: General Electric Company
    Inventors: John Carl Glessner, Jarrod Paul Sands
  • Patent number: 10107198
    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: October 23, 2018
    Assignee: United Technologies Corporation
    Inventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney