Patents Examined by Ehud Gartenberg
  • Start biased liquid fuel manifold for a gas turbine engine
    Patent number: 10428738
    Abstract: A fuel distribution manifold for a gas turbine engine is disclosed herein. The fuel distribution manifold includes a manifold body, a stage divider, and a plurality of manifold outlet ports. The stage divider subdivides an internal volume of the manifold body into a primary stage volume and a secondary stage volume. A majority of the plurality of manifold outlet ports extends from the manifold body between the primary inlet port and the stage divider, each being fluidly connected to the primary stage volume. A remainder of the plurality of manifold outlet ports extends from the manifold body between the secondary inlet port and the stage divider, each being fluidly connected to the secondary stage volume.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: October 1, 2019
    Assignee: Solar Turbines Incorporated
    Inventors: Anthony P. Batakis, Dietmar Karl Sauer
  • Unitary flow path structure
    Patent number: 10378770
    Abstract: Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The inner wall and the unitary outer wall define a combustor of the combustion section. In another exemplary embodiment, a flow path assembly comprises a unitary inner wall defining an inner boundary of a flow path and extending from a forward end of a combustor through a nozzle portion of a first turbine stage, and a unitary outer wall defining an outer boundary of the flow path and extending from the forward end of the combustor through at least the first turbine stage.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Andrew Scott Bilse, Mark Eugene Noe, Brett Joseph Geiser
  • Fuel injector assembly
    Patent number: 10317081
    Abstract: A fuel injector assembly for a combustor is provided, including a fuel nozzle having an axial inflow swirler and one or more radial inflow swirlers spaced radially outward of the downstream end of the fuel nozzle and mounted to the combustor, wherein the airstreams produced by the swirlers airblast atomize fuel films produced by the fuel nozzle.
    Type: Grant
    Filed: January 26, 2011
    Date of Patent: June 11, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: James B. Hoke
  • Gas turbine engine and annular combustor with swirler
    Patent number: 10295191
    Abstract: A combustor is provided in which a fuel and working fluid can be injected in an annulus. In one form the fuel and working fluid is circumferentially flowed within the annulus and traverses the annulus in an axial direction from one side to another side where the flow exits. The working fluid and air can be co-axially admitted to the combustor and in one form the working fluid can be swirled about the fuel dispensed from a fuel injector. The combustor can provide for a rich burning zone. In one embodiment the combustor is configured as an inter-turbine combustor having an outlet at one axial side of the combustor. A lean burn region can be created within a flow path of the turbine.
    Type: Grant
    Filed: December 31, 2011
    Date of Patent: May 21, 2019
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: Jushan Chin
  • Particle separating fluid intake
    Patent number: 10287980
    Abstract: A fluid intake including first and second ducts and a particle separation spinner defining an interface between the first and second ducts is disclosed. Spinner includes flow passages passing from first duct side of the spinner to second duct side of the spinner and splitter bodies separating the flow passages. Flow passages and splitter bodies are arranged in thread-like screw manner about spinner. In use, the spinner is spun about an axis of rotation, axis and direction of rotation being such that, from static frame of reference with respect to first duct, splitter bodies and flow passages have a component of movement towards a main travel direction of a fluid flow incident towards spinner from first duct. Splitter bodies are arranged such that they oblige fluid in the fluid flow to follow a convoluted path if it is to pass from first duct to second duct via the flow passages.
    Type: Grant
    Filed: January 31, 2016
    Date of Patent: May 14, 2019
    Assignee: ROLLS-ROYCE PLC
    Inventor: Gordon David Warnes
  • System and method for a fluidic barrier from the upstream splitter
    Patent number: 10280872
    Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of high pressure fluid jets originating from a trailing edge of the upstream splitter, the jets restricting the migration of the core stream into the bypass stream through the fluid passage.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: May 7, 2019
    Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventor: Edward C. Rice
  • System and method for creating a fluidic barrier with vortices from the upstream splitter
    Patent number: 10267159
    Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of surface interruptions on a core side surface of the upstream splitter and a plurality of vortices originating from the surface interruptions, thereby restricting the migration of the core stream into the bypass stream through the fluid passage.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: April 23, 2019
    Assignee: ROLLS-ROYCE NORTH AMERICA TECHNOLOGIES INC.
    Inventor: Edward C. Rice
  • Gas turbine engine combustor with tailored temperature profile
    Patent number: 10260748
    Abstract: A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.
    Type: Grant
    Filed: December 21, 2012
    Date of Patent: April 16, 2019
    Assignee: United Technologies Corporation
    Inventors: Timothy S. Snyder, Randal G. McKinney, James B. Hoke
  • Methods and assemblies for attaching airfoils within a flow path
    Patent number: 10253641
    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
  • Airfoil fluid curtain to mitigate or prevent flow path leakage
    Patent number: 10253643
    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path.
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Daniel Patrick Kerns, Brandon ALlanson Reynolds
  • Methods and features for positioning a flow path inner boundary within a flow path assembly
    Patent number: 10247019
    Abstract: Flow path assemblies and methods for assembling a flow path assembly of a gas turbine engine are provided. For example, a flow path assembly comprises a unitary outer wall including combustor and turbine portions that are integrally formed as a single unitary structure; a single piece, generally annular inner band; and a plurality of nozzle airfoils extending from the unitary outer wall to the inner band. Each nozzle airfoil interfaces with the inner band to position the inner band within the assembly. An exemplary assembly method comprises inserting an inner band into a flow path having a unitary outer wall as its outer boundary; inserting a plurality of nozzle airfoils into the flow path; and securing the nozzle airfoils with respect to the unitary outer wall. The inner band interfaces with an inner end of each nozzle airfoil to radially locate the inner band within the flow path.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: April 2, 2019
    Assignee: General Electric Company
    Inventors: Jason David Shapiro, Brandon ALlanson Reynolds, Jonathan David Baldiga
  • Monitoring system for non-ferrous metal particles
    Patent number: 10233773
    Abstract: According to one aspect of the present disclosure, a debris monitoring system is disclosed that includes a fan, a geared architecture operatively coupled to the fan. The geared architecture includes a component having a non-ferrous metal coating. A scavenge pump is in fluid communication with the geared architecture via a lubrication sump. A non-ferrous chip detector is situated downstream of the geared architecture, but upstream of the scavenge pump. A controller is configured to determine a lubrication condition of the component based on a signal received from the non-ferrous chip detector, and command a status indicator in response thereto.
    Type: Grant
    Filed: November 17, 2015
    Date of Patent: March 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • System and method for creating a fluidic barrier from the leading edge of a fan blade
    Patent number: 10233869
    Abstract: A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of vortex generators, each of the vortex generators positioned on the leading edge of a respective fan blade proximate the upstream splitter and the core stream restricting the migration of the core stream into the bypass stream through the fluid passage.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: March 19, 2019
    Assignee: ROLLS ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventor: Edward C. Rice
  • Low NOturbine exhaust fuel burner assembly
    Patent number: 10227922
    Abstract: A low NOX burner in which the amount of air flow to the low NOX (nitrous oxides) burner can be adjusted (e.g., based on determinations related to the TEG air flow to the low NOX burner). A low NOX burner capable of operating in a TEG mode that uses a mixture of fresh air and turbine exhaust gas (TEG) as an oxidizer, and also in a fresh air mode in which fresh air (but not TEG) is used as an oxidizer (e.g., and that may be configured to switch seamlessly between these modes). A method of operating a low NOx burner that that includes using TEG and fresh air as an oxidizer to burn fuel, in a TEG mode and, when conditions dictate, such as when the TEG flow has decreased to a pre-determined level (e.g., zero or close to zero), switching from the TEG mode to a fresh air mode.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: March 12, 2019
    Assignee: JOHN ZINK COMPANY, LLC
    Inventor: Matt Whelan
  • Turbine engine, such as a turbojet or a turboprop engine
    Patent number: 10190430
    Abstract: A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims.
    Type: Grant
    Filed: April 9, 2013
    Date of Patent: January 29, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Francois Leglaye, Emeric D'Herbigny
  • Attachment stud on a combustor floatwall panel with internal cooling holes
    Patent number: 10190773
    Abstract: A combustor floatwall panel includes a stack of layers of a sintered material forming in the aggregate a panel, an attachment stud, and a cooling flow passageway. The panel has a first surface and a second surface parallel to the first surface. The attachment stud projects from the second surface. The cooling flow passageway includes a feeder hole extending through the attachment stud, and at least one effusion cooling hole extending to the first surface. The effusion cooling hole is fluidly connected to the feeder hole. The effusion cooling hole extends along a first axis where the effusion cooling hole meets the first surface. The feeder hole extends along a second axis. The first axis is at a first angle relative to the first surface. The second axis is at a second angle relative to the first surface. The second angle is greater than the first angle.
    Type: Grant
    Filed: October 23, 2014
    Date of Patent: January 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Russell B. Hanson, George F. Titterton, III
  • Combustor heat shield sealing
    Patent number: 10184661
    Abstract: A method and an apparatus for reducing airflow leakage between a combustor liner and a rail of a heat shield mounted to an inner surface of the combustor liner. The method comprises locally deforming the combustor liner in sealing engagement with the rail by applying a pressure on the outer surface of the combustor liner over the rail of the heat shield. A tool, such as a sealing clip, may be mounted in pressing engagement with the outer surface of the combustor liner to apply forces locally on the liner over the rail of the heat shield.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: January 22, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Daniel Hayek, Jason Herborth, Yen-Wen Wang
  • Gas turbine engine uncontrolled high thrust accommodation system and method
    Patent number: 10156190
    Abstract: A system and method of accommodating an uncontrolled high thrust condition in a turbofan gas turbine engine includes processing engine data from the turbofan gas turbine engine to determine when a potential for an uncontrolled high thrust condition exists. When the potential for an uncontrolled high thrust condition exists, the engine data are processed to determine whether corrective action for the uncontrolled high thrust condition should be implemented by varying turbofan gas turbine engine effective geometry to (i) increase turbofan gas turbine engine rotational speed or (ii) decrease turbofan gas turbine engine rotational speed. The determined corrective action is automatically implemented.
    Type: Grant
    Filed: May 20, 2015
    Date of Patent: December 18, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Scot Coffey, Gregory J. Chapman, Yufei Xiong
  • Apparatus and methods for treating and/or utilizing a gaseous medium
    Patent number: 10151488
    Abstract: Example apparatus and methods providing for the improved chemical conversion of the combustible components of a gaseous medium are disclosed. In some examples, the apparatus includes a guiding body that guides the flow of the gaseous medium within a reaction chamber of the apparatus. In some examples, the guiding body of the disclosed apparatus is configured to stabilize a residence period of the gaseous medium in the reaction chamber. In some examples, the guiding body results in a flow path of the gaseous medium within the reaction chamber being optimized and/or maximized, and/or results in a short circuit flow of the gaseous medium in the reaction chamber being suppressed. In some disclosed examples, the guiding body causes at least a portion of the flow path of the gaseous medium within the reaction chamber to take the form of a cyclone flow.
    Type: Grant
    Filed: August 24, 2015
    Date of Patent: December 11, 2018
    Assignee: DÜRR SYSTEMS GMBH
    Inventors: Axel Widenhorn, Roland Stoll
  • Annular combustion chamber
    Patent number: 10151485
    Abstract: A turbine engine having an annular combustion chamber formed by two coaxial annular shrouds, an inner shroud and an outer shroud relative to the axis of the turbine engine, which shrouds are arranged one inside the other and are connected together at their upstream ends by an annular chamber end wall that is fastened to an outer casing surrounding the outer annular shroud, the downstream ends of the inner and outer annular shrouds being connected to flanges fastened to an inner casing and to the outer casing, respectively. The upstream end of at least one of the inner and outer shrouds is centered by bearing radially against the annular chamber end wall and co-operates therewith in leaktight axial sliding.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: December 11, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Nicolas Lunel, Denis Jean Maurice Sandelis