Patents by Inventor Steven Bruce

Steven Bruce has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Convective shielding cooling hole pattern
    Patent number: 9482098
    Abstract: The cooling system for a turbine may include a plurality of platform cooling openings positioned in a platform of the turbine airfoil. In particular, the first set of cooling openings may create a first cooling path and a second set of cooling openings may be placed in the path of the first cooling path where the first cooling flow will cool the second set of cooling openings.
    Type: Grant
    Filed: May 11, 2012
    Date of Patent: November 1, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Steven Bruce Gautschi, Christina E. Botnick
  • INCIDENT TOLERANT TURBINE VANE GAP FLOW DISCOURAGEMENT
    Publication number: 20160251980
    Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.
    Type: Application
    Filed: October 17, 2014
    Publication date: September 1, 2016
    Inventors: Thomas N. Slavens, Steven Bruce Gautschi
  • GAS TURBINE ENGINE AIRFOIL COOLING CONFIGURATION WITH PRESSURE GRADIENT SEPARATORS
    Publication number: 20160251968
    Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.
    Type: Application
    Filed: February 26, 2015
    Publication date: September 1, 2016
    Inventors: San Quach, Ryan Alan Waite, Christopher King, Steven Bruce Gautschi
  • Turbine airfoil tip shelf and squealer pocket cooling
    Patent number: 9429027
    Abstract: An airfoil includes a pressure surface and a suction surface extending from a root section of the airfoil to a tip section of the airfoil. The airfoil also includes a leading edge and a trailing edge defining a chord length of the airfoil therebetween. The airfoil further includes a tip shelf formed along the tip section of the airfoil between the pressure surface and a tip shelf wall. The tip shelf wall is spaced between the pressure surface and the suction surface and the tip shelf extends from within 10% of the chord length measured from the leading edge to within 10% of the chord length measured from the trailing edge.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: August 30, 2016
    Assignee: United Technologies Corporation
    Inventors: Dominic J. Mongillo, Jr., Steven Bruce Gautschi, San Quach
  • Lost Core Molding Cores for Forming Cooling Passages
    Publication number: 20160228941
    Abstract: In a featured embodiment, a lost core assembly includes a ceramic component having a tapered shape in a radial direction. A refractory metal component extends radially from the ceramic core component. A method of molding a gas turbine engine component is also disclosed.
    Type: Application
    Filed: September 26, 2014
    Publication date: August 11, 2016
    Inventors: Lane THORNTON, San QUACH, Steven Bruce GAUTSCHI
  • FLARED CROSSOVERS FOR AIRFOILS
    Publication number: 20160230565
    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section having an external wall and an internal wall. The internal wall defines a reference plane extending in a spanwise direction along a surface of the internal wall, a first cavity and a second cavity separated by the internal wall, and a plurality of crossover passages within the internal wall and connecting the first cavity to the second cavity. Each of the plurality of crossover passages defines a passage axis. The passage axis of each of the plurality of crossover passages is arranged at a radial angle relative to a localized region of the reference plane such that the radial angle of at least some of the plurality of crossover passages differs in the spanwise direction.
    Type: Application
    Filed: February 10, 2015
    Publication date: August 11, 2016
    Inventors: Christopher King, San Quach, Steven Bruce Gautschi
  • ROTATING TURBINE VANE BEARING COOLING
    Publication number: 20160222825
    Abstract: A pivoting turbine vane has an airfoil, an inner bearing race and an outer bearing race, with the inner and outer bearing races on a pivot axis of the pivoting turbine vane. There are cooling air passages through at least one of the inner and outer bearing races to provide cooling air from a remote facing face of at least one of the inner and outer bearing races to an airfoil facing face of at least one of the inner and outer bearing races. A turbine section is also disclosed.
    Type: Application
    Filed: September 22, 2014
    Publication date: August 4, 2016
    Inventors: Thomas N. Slavens, Steven Bruce Gautschi
  • INCIDENCE TOLERANT ENGINE COMPONENT
    Publication number: 20160222794
    Abstract: This disclosure relates to a gas turbine engine including a component having a leading edge, a pressure side and a suction side opposite the pressure side. The component includes a first group of showerhead holes in the leading edge and a second group of showerhead holes in one of the pressure side and the suction side. The component further includes a first core passageway and a second core passageway separate from the first core passageway. The first core passageway and the second core passageway are in communication with a respective one of the first group of showerhead holes and the second group of showerhead holes.
    Type: Application
    Filed: September 9, 2014
    Publication date: August 4, 2016
    Inventors: Thomas N. Slavens, Mark F. Zelesky, Atul Kohli, Sean D. Bradshaw, Steven Bruce Gautschi
  • LOW DIAMETER OPTICAL FIBER
    Publication number: 20160216442
    Abstract: Small-radius coated optical fibers having large mode field diameter and low bending losses. The coated fiber may have an outer radius of 110 ?m or less, while providing a mode field diameter of 9.0 ?m or greater and a bending loss when wrapped about a 15 mm mandrel of 0.5 dB/km or less at wavelength of 1550 nm. The coated fiber may have a mode field diameter of 9.2 ?m or greater and may have a bending loss at 1550 nm of 0.25 dB/km or less when wrapped about a 20 mm mandrel or a bending loss at 1550 nm of 0.02 dB/km or less when wrapped about a 30 mm mandrel.
    Type: Application
    Filed: May 7, 2015
    Publication date: July 28, 2016
    Inventors: Dana Craig Bookbinder, Steven Bruce Dawes, Inna Igorevna Kouzmina, Ming-Jun Li, Manuela Ocampo, Pushkar Tandon
  • INTERNAL COOLING CAVITY WITH TRIP STRIPS
    Publication number: 20160208619
    Abstract: An airfoil is provided. The airfoil may comprise a cross over, an impingement chamber in fluid communication with the cross over, and a first trip strip disposed on a first surface of the impingement chamber. A cooling system is also provided. The cooling system may comprise an impingement chamber, a first trip strip on a first surface of the impingement chamber, and a second trip strip on a second surface of the impingement chamber. An internally cooled engine part is further provided. The internally cooled part may comprise a cross over and an impingement chamber in fluid communication with the cross over. The cross over may be configured to direct air towards a first surface of the impingement chamber. A first trip strip may be disposed on the first surface of the impingement chamber.
    Type: Application
    Filed: January 21, 2015
    Publication date: July 21, 2016
    Applicant: United Technologies Corporation
    Inventors: San Quach, Atul Kohli, Matthew A. Devore, Steven Bruce Gautschi
  • AIRFOIL SHOWERHEAD PATTERN APPARATUS AND SYSTEM
    Publication number: 20160177734
    Abstract: The systems and methods described herein adapt the orientation, position and/or diffusion angles of showerhead cooling holes depending on the external gas/streamline flow direction. In regions, for example, where the stagnation line is on the pressure side, the breakouts of the showerhead holes substantially face aft (e.g., primarily towards the suction side). The location and positioning of the holes may be oriented according to the direction of incoming gas flows.
    Type: Application
    Filed: September 23, 2015
    Publication date: June 23, 2016
    Applicant: United Technologies Corporation
    Inventors: San Quach, Christopher King, Steven Bruce Gautschi, David J. Candelori
  • ANTIBODY DRUG CONJUGATES
    Publication number: 20160137730
    Abstract: This application discloses anti-P-cadherin antibodies, antigen binding fragments thereof, and antibody drug conjugates of said antibodies or antigen binding fragments. The invention also relates to methods of treating cancer using the antibodies, antigen binding fragments, and antibody drug conjugates. Also disclosed herein are methods of making the antibodies, antigen binding fragments, and antibody drug conjugates, and methods of using the antibodies and antigen binding fragments as diagnostic reagents.
    Type: Application
    Filed: November 13, 2015
    Publication date: May 19, 2016
    Applicant: Novartis AG
    Inventors: Tinya ABRAMS, Steven Bruce Cohen, Jason Damiano, Clemens Dürr, Thomas Huber, Daniel Menezes, Kathy Miller, Katherine Rendahl, Jean-Michel Rene Rondeau
  • Trailing edge or tip flag antiflow separation
    Patent number: 9328617
    Abstract: An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.
    Type: Grant
    Filed: March 20, 2012
    Date of Patent: May 3, 2016
    Assignee: United Technologies Corporation
    Inventors: Steven Bruce Gautschi, Brandon W. Spangler, San Quach, Dominic J. Mongillo, Jr.
  • HYGROSCOPIC ADDITIVES FOR SILICA SOOT COMPACTS AND METHODS FOR FORMING OPTICAL QUALITY GLASS
    Publication number: 20160115070
    Abstract: A method for forming an optical quality glass is provided. The method includes contacting silica soot particles with a hygroscopic additive, forming a silica soot compact, and removing the hygroscopic additive from the silica soot compact. A method of forming a cladding portion of an optical fiber preform is also provided.
    Type: Application
    Filed: October 8, 2015
    Publication date: April 28, 2016
    Inventors: Steven Bruce Dawes, Lisa Ann Hogue
  • High pressure wafer style magnetic flowmeter
    Patent number: 9316514
    Abstract: A wafer-type electromagnetic flow sensor includes a single-piece chassis having a pair of faces and a flow conduit extending between the pair of faces. Each face of the chasses includes a feature configured to engage a metal sealing ring. A non-conductive liner is disposed in the flow conduit of the single-piece chassis. A plurality of electromagnetic coils is configured to generate a flux into process fluid flowing through the flow conduit. A pair of electrodes is configured to electrically couple to the process fluid. A feedthrough assembly is configured to maintain process fluid pressure while allowing a plurality of electrical conductors to pass therethrough.
    Type: Grant
    Filed: March 26, 2014
    Date of Patent: April 19, 2016
    Assignee: ROSEMOUNT INC.
    Inventors: Joseph Alan Smith, Steven Bruce Rogers, Jesse Christopher Pettit, Nelson Mauricio Morales
  • Gas turbine engine airfoil impingement cooling
    Patent number: 9296039
    Abstract: An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: March 29, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Mark F. Zelesky, Dominic J. Mongillo, Jr., Matthew A. Devore, Steven Bruce Gautschi, Benjamin T. Fisk
  • PLATE FOR METERING FLOW
    Publication number: 20160084164
    Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.
    Type: Application
    Filed: August 3, 2015
    Publication date: March 24, 2016
    Inventors: Thomas N. Slavens, Dominic J. Mongillo, Steven Bruce Gautschi, Jaime G. Ghigliotty
  • Turbine airfoil tip shelf and squealer pocket cooling
    Patent number: 9284845
    Abstract: An airfoil comprises pressure and suction surfaces extending from a root section to a tip section of the airfoil. The airfoil also comprises a leading edge and trailing edge defining a chord length therebetween. A tip shelf is formed along the tip section between the pressure surface and a tip shelf wall, the tip shelf wall being spaced between the pressure surface and the suction surface. A squealer pocket is formed along the tip section between the tip shelf wall and a squealer tip wall extending from the suction surface. The tip shelf extends from within 10% of the cord length measured from the leading edge to within 10% of the chord length measured from the trailing edge. The squealer pocket extends from within 10% of the chord length measured from the leading edge to terminate less than 85% of the chord length measured from the trailing edge.
    Type: Grant
    Filed: April 10, 2014
    Date of Patent: March 15, 2016
    Assignee: United Technologies Corporation
    Inventors: Scott D. Lewis, Dominic J. Mongillo, Jr., Steven Bruce Gautschi, Christopher Corcoran
  • SPLAYED TIP FEATURES FOR GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160069189
    Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.
    Type: Application
    Filed: February 25, 2015
    Publication date: March 10, 2016
    Inventors: San Quach, Tracy A Propheter-Hinckley, Dominic J Mongillo, JR., Steven Bruce Gautschi
  • DISK LUG IMPINGEMENT FOR GAS TURBINE ENGINE AIRFOIL
    Publication number: 20160040534
    Abstract: A component for a gas turbine engine includes a root with a neck that extends into a fir tree with at least one tooth, the root includes a feed passage in communication with a multiple of cooling passages that extend through the neck and fir tree.
    Type: Application
    Filed: April 10, 2015
    Publication date: February 11, 2016
    Inventors: Steven Bruce Gautschi, San Quach, Tracy A. Propheter-Hinckley