Patents by Inventor San Quach

San Quach 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).

  • DIRECTIONAL COOLING ARRANGEMENT FOR AIRFOILS
    Publication number: 20190055845
    Abstract: An airfoil according to an example of the present disclosure includes, among other things, an internal wall and an external wall. The external wall defines pressure and suction sides between a leading edge and a trailing edge, and the airfoil section defines a mean camber line that extends between the leading and trailing edges to bisect a thickness of the airfoil section. A first cavity and a second cavity are separated by the internal wall. The second cavity is bounded by the external wall at the leading edge. At least one crossover passage within the internal wall connects the first cavity to the second cavity. The crossover passage defines a passage axis. The passage axis defines a passage angle with respect to the mean camber line such that the passage axis extends transversely from the mean camber line to intersect a surface of the second cavity.
    Type: Application
    Filed: August 17, 2017
    Publication date: February 21, 2019
    Inventors: San Quach, Alberto A. Mateo, Jeffrey T. Morton, Jason Shenny, Gregory Anselmi
  • Cooling for gas turbine engine components
    Patent number: 10196902
    Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.
    Type: Grant
    Filed: September 15, 2015
    Date of Patent: February 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sasha M. Moore, Timothy J. Jennings, Thomas N. Slavens, Clifford J. Musto, Nicholas M. LoRicco, Carey Clum, John McBrien, Christopher Whitfield, San Quach
  • Heat transfer pedestals with flow guide features
    Patent number: 10196900
    Abstract: A turbomachine component includes a body defining an interior cooling channel in fluid communication with the exterior of the body for fluid communication with a cooling flow source. At least one flow modifying pedestal is disposed within the interior cooling channel extending in a first direction. The flow modifying pedestal includes at least one flow feature that extends from the pedestal in a second direction.
    Type: Grant
    Filed: October 14, 2015
    Date of Patent: February 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher King, San Quach
  • Flared crossovers for airfoils
    Patent number: 10190420
    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: Grant
    Filed: February 10, 2015
    Date of Patent: January 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher King, San Quach, Steven Bruce Gautschi
  • GAS TURBINE ENGINE COMPONENT COOLING CIRCUIT
    Publication number: 20190017390
    Abstract: A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.
    Type: Application
    Filed: June 5, 2018
    Publication date: January 17, 2019
    Inventors: Tracy A. Propheter-Hinckley, Steven Bruce Gautschi, San Quach
  • HELICAL SKIN COOLING PASSAGES FOR TURBINE AIRFOILS
    Publication number: 20190003316
    Abstract: An airfoil for a gas turbine engine may comprise an airfoil body having an outer diameter (OD) end extending between a leading edge and a trailing edge and having an ID end located opposite the airfoil body from the OD end. The airfoil body defines a helical skin cooling passage extending between the ID end of the airfoil and the OD end of the airfoil. The airfoil body may further define a main body core. The helical skin cooling passage may thermally shield the main body core.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 3, 2019
    Applicant: United Technologies Corporation
    Inventors: Jeffrey T. Morton, San Quach
  • COMBUSTOR LINER PANEL END RAIL WITH DIFFUSED INTERFACE PASSAGE FOR A GAS TURBINE ENGINE COMBUSTOR
    Publication number: 20180363902
    Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel including a cold side; and a rail that extends from the cold side, the rail includes a first diffusion interface passage surface and a second diffusion interface passage surface, the first diffusion interface passage surface angled with respect to the second diffusion interface passage surface.
    Type: Application
    Filed: June 15, 2017
    Publication date: December 20, 2018
    Applicant: United Technologies Corporation
    Inventors: Donald W. Peters, San Quach, Jeffrey T. Morton, Matthew D. Parekh
  • Turbine airfoil and method of cooling
    Patent number: 10156144
    Abstract: An airfoil for use in a gas turbine engine is provided. The airfoil having: a pressure surface and a suction surface each extending axially from a leading edge to a trailing edge of the airfoil, at least one of the pressure surface, the suction surface, the leading edge and the trailing edge terminating at an edge of a tip section of the airfoil; a plurality of internal cooling channels located within the airfoil; and at least one cooling hole in fluid communication with at least one of the plurality of internal cooling channels, wherein the at least one cooling hole is aligned with an opening or diffuser that extends directly from the at least one cooling hole and wherein the opening or diffuser is formed in and extends through the edge of the tip section of the airfoil.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: December 18, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Steven Bruce Gautschi, Matthew A. Devore, Scott D. Lewis, Matthew S. Gleiner, Christopher King, Christopher Corcoran, David Donald Chapdelaine
  • COMBUSTOR PANEL ENDRAIL INTERFACE
    Publication number: 20180335211
    Abstract: A combustor of a gas turbine engine may include a combustor shell, a first combustor panel coupled to the combustor shell, and a second combustor panel coupled to the combustor shell. The first combustor panel may have a first endrail and the second combustor panel may have a second endrail. An annular cooling cavity may be defined between the combustor shell and the first and second combustor panels and a channel may be defined between the first endrail and the second endrail, wherein direct line-of-sight through the channel from the annular cooling cavity to a combustor chamber is obstructed. Said differently, the interface between the adjacent endrails may be non-linear, in a direction from the annular cooling cavity to the combustor chamber.
    Type: Application
    Filed: May 18, 2017
    Publication date: November 22, 2018
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: SAN QUACH, JEFFREY T. MORTON, MATTHEW D. PAREKH
  • REDUNDANT ENDRAIL FOR COMBUSTOR PANEL
    Publication number: 20180335212
    Abstract: A combustor panel may include a body having an edge, a first endrail disposed along the edge of the body, and a second endrail disposed adjacent the first endrail, wherein a volume is defined between the first endrail and the second endrail. The first endrail may have a first height, measured from the body to a first tip of the first endrail, and the second endrail may have a second height, measured from the body to a second tip of the second endrail, wherein the first height is the same as the second height. The second endrail may include an endrail hole extending through the second endrail.
    Type: Application
    Filed: May 18, 2017
    Publication date: November 22, 2018
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: SAN QUACH, JEFFREY T. MORTON
  • Cooling hole arrangement for engine component
    Patent number: 10125614
    Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: November 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, San Quach, Steven Bruce Gautschi, Brandon S. Donnell, Anita L. Tracy, Yafet Girma
  • AIRFOIL FOR GAS TURBINE ENGINE
    Publication number: 20180320529
    Abstract: An airfoil includes a leading edge and a trailing edge. A first exterior wall extends between the leading edge and the trailing edge. A second exterior wall opposite the first exterior wall extends between the leading edge and the trailing edge. A first cavity is adjacent the first exterior wall and includes a central portion and at least one forward extending slot passage and at least one aft extending slot passage.
    Type: Application
    Filed: May 2, 2017
    Publication date: November 8, 2018
    Inventors: San Quach, Tracy A. Propheter-Hinckley
  • COMBUSTOR LINER PANEL END RAIL MATCHING HEAT TRANSFER FEATURES
    Publication number: 20180306113
    Abstract: A combustor section of a turbine engine includes a first liner panel including a first end rail. The first end rail includes a protruding heat transfer feature. A second liner panel includes a second end rail disposed proximate the first end rail. The second end rail includes a recess matching the protruding heat transfer feature of the first end rail. A turbine engine and a method of assembling a combustor assembly of a gas turbine engine are also disclosed.
    Type: Application
    Filed: April 19, 2017
    Publication date: October 25, 2018
    Inventors: Jeffrey T. Morton, San Quach
  • Gas turbine engine component cooling circuit
    Patent number: 10100646
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity and a microcircuit in fluid communication with the first cavity. A plunged hole intersects at least a portion of the microcircuit.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: October 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Tracy A. Propheter-Hinckley, Steven Bruce Gautschi, San Quach
  • PANEL SURFACE POCKETS FOR COATING RETENTION
    Publication number: 20180283688
    Abstract: A coated panel for a gas turbine engine includes a panel having a panel inner surface and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is disposed within the pocket to enhance coating retention to the panel. A gas turbine engine includes a turbine, a combustor to supply hot combustion gases to the turbine along a gas path, and one or more coated panels located along the gas path. The one or more panels includes a panel having a panel inner surface, and a pocket formed in the panel inner surface, the pocket having a pocket depth. A coating is applied to the pocket such that a coating edge is located within the pocket to enhance coating retention to the panel.
    Type: Application
    Filed: April 3, 2017
    Publication date: October 4, 2018
    Inventors: San Quach, Andreas Sadil, Donald W. Peters
  • COMBUSTION PANEL GROMMET
    Publication number: 20180283695
    Abstract: A gas turbine engine and a combustor panel assembly are disclosed. The gas turbine engine includes a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.
    Type: Application
    Filed: April 3, 2017
    Publication date: October 4, 2018
    Inventors: San Quach, Robert M. Sonntag, Donald W. Peters
  • LOST CORE MOLDING CORES FOR FORMING COOLING PASSAGES
    Publication number: 20180281051
    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: April 24, 2018
    Publication date: October 4, 2018
    Inventors: Lane Thornton, San Quach, Steven Bruce Gautschi
  • AIRFOIL TIP POCKET WITH AUGMENTATION FEATURES
    Publication number: 20180274373
    Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
    Type: Application
    Filed: June 1, 2018
    Publication date: September 27, 2018
    Inventors: San Quach, Tracy A. Propheter-Hinckley, Steven Bruce Gautschi
  • COMBUSTOR LINER PANEL END RAIL ANGLED COOLING INTERFACE PASSAGE FOR A GAS TURBINE ENGINE COMBUSTOR
    Publication number: 20180238545
    Abstract: A combustor for a gas turbine engine includes a support shell with an angled shell interface; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel adjacent to the angled shell interface; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail adjacent to the angled shell interface.
    Type: Application
    Filed: February 23, 2017
    Publication date: August 23, 2018
    Applicant: United Technologies Corporation
    Inventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh
  • COMBUSTOR LINER PANEL END RAIL COOLING INTERFACE PASSAGE FOR A GAS TURBINE ENGINE COMBUSTOR
    Publication number: 20180238547
    Abstract: A combustor for a gas turbine engine includes a support shell; a first liner panel mounted to the support shell via a multiple of studs, the first liner panel including a first rail that extends from a cold side of the first liner panel; and a second liner panel mounted to the support shell via a multiple of studs, the second liner panel including a second rail that extends from a cold side of the second liner panel adjacent to said first rail, the second rail includes a discontinuous rail end surface.
    Type: Application
    Filed: February 23, 2017
    Publication date: August 23, 2018
    Applicant: United Technologies Corporation
    Inventors: San Quach, Jeffrey T. Morton, Matthew D. Parekh