Patents by Inventor Lisa P. O'Neill

Lisa P. O'Neill 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).

  • Patent number: 11434774
    Abstract: Borescope plugs are described. The borescope plugs include a borescope plug base having a first side configured to support a shank and a second side having a centroid defined as the center of the borescope plug base, a first mounting aperture formed in the second side, and a second mounting aperture formed in the second side. The first and second mounting apertures are configured to each receive a fastener to mount the borescope plug base to a case, and an offset line drawn through the center of the first mounting aperture and through the center of the second mounting aperture does not pass through the centroid or does not include a point defined by the centroid.
    Type: Grant
    Filed: November 28, 2018
    Date of Patent: September 6, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Lisa P. O'Neill, Amarnath Ramlogan
  • Publication number: 20210033283
    Abstract: Heatshields for installation within gas turbine engines are described. The heatshields include a metal body having a first end, a second end, a first side, and a second side, wherein the first side and the second side define parallel sides extending from the first end to the second end, an engagement portion formed along the first side and arranged to engage with a portion of a case, a shielding portion formed along the second side, and a mid-body portion extending between the engagement portion and the shielding portion and has an arcuate shape in cross-section. The metal body is configured to form a hoop, split-ring structure with the first end attached to the second end.
    Type: Application
    Filed: July 30, 2019
    Publication date: February 4, 2021
    Inventors: Donna J. Chavez, Lisa P. O'Neill
  • Patent number: 10502090
    Abstract: A borescope plug for a gas turbine engine includes a base attachable to a case and defining a base cavity, a shank having a base engagement element at a first end of the shank, and a plug member located at a second end of the shank, the plug member configured to plug a borescope aperture in a borescope vane cluster. The base engagement element fits within the base cavity such that the base moveably retains the base engagement element and wherein the base engagement element can move within the base cavity.
    Type: Grant
    Filed: August 8, 2016
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Fabian D. Betancourt, Amarnath Ramlogan, Lisa P. O'Neill
  • Publication number: 20190093491
    Abstract: Borescope plugs are described. The borescope plugs include a borescope plug base having a first side configured to support a shank and a second side having a centroid defined as the center of the borescope plug base, a first mounting aperture formed in the second side, and a second mounting aperture formed in the second side. The first and second mounting apertures are configured to each receive a fastener to mount the borescope plug base to a case, and an offset line drawn through the center of the first mounting aperture and through the center of the second mounting aperture does not pass through the centroid or does not include a point defined by the centroid.
    Type: Application
    Filed: November 28, 2018
    Publication date: March 28, 2019
    Inventors: Lisa P. O'Neill, Amarnath Ramlogan
  • Patent number: 10047617
    Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.
    Type: Grant
    Filed: April 7, 2014
    Date of Patent: August 14, 2018
    Assignee: United Technologies Corporation
    Inventors: Ky H. Vu, Lisa P. O'Neill, Takao Fukuda, Gerald M. Mace, Jr., Andy Turko, Andrew P. Boursy, Lynn M. Boy
  • Publication number: 20180038241
    Abstract: A borescope plug for a gas turbine engine includes a base attachable to a case and defining a base cavity, a shank having a base engagement element at a first end of the shank, and a plug member located at a second end of the shank, the plug member configured to plug a borescope aperture in a borescope vane cluster. The base engagement element fits within the base cavity such that the base moveably retains the base engagement element and wherein the base engagement element can move within the base cavity.
    Type: Application
    Filed: August 8, 2016
    Publication date: February 8, 2018
    Inventors: Fabian D. Betancourt, Amarnath Ramlogan, Lisa P. O'Neill
  • Publication number: 20160053621
    Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.
    Type: Application
    Filed: April 7, 2014
    Publication date: February 25, 2016
    Inventors: Ky H. Vu, Lisa P. O'Neill, Takao Fukuda, Gerald M. Mace, Jr., Andy Turko, Andrew P. Boursy, Lynn M. Boy
  • Patent number: 8439629
    Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.
    Type: Grant
    Filed: March 1, 2007
    Date of Patent: May 14, 2013
    Assignee: United Technologies Corporation
    Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
  • Patent number: 8123466
    Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.
    Type: Grant
    Filed: March 1, 2007
    Date of Patent: February 28, 2012
    Assignee: United Technologies Corporation
    Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
  • Publication number: 20090067994
    Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.
    Type: Application
    Filed: March 1, 2007
    Publication date: March 12, 2009
    Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
  • Patent number: 7467924
    Abstract: The present invention provides a turbine blade having a revised under-platform structure including a unique coating combination that reduces mechanical stress factors within the turbine blade. The turbine blade includes a platform with an airfoil extending upwardly from the airfoil and a root portion extending downwardly from the platform. Two suction side tabs extend a first distance outward from a suction side of the root potion. Two pressure side tabs extend outward from a pressure side of the root portion. One of the two pressure side tabs extends outward a distance similar to the first distance, however, the other of the two pressure side tabs extends outward a distance much smaller than the first distance, which reduces stresses acting on the turbine blade. In addition, a plurality of coatings are systematically applied to the turbine blade to further reduce mechanical stress factors and improve cooling.
    Type: Grant
    Filed: August 16, 2005
    Date of Patent: December 23, 2008
    Assignee: United Technologies Corporation
    Inventors: Robert A. Charbonneau, Kenneth P. Botticello, Shawn J. Gregg, Kirk David Hlavaty, Jeffrey R. Levine, Kenneth A. Lonczak, Craig R. McGarrah, Dominic J. Mongillo, Lisa P. O'Neill, Edward Pietraszkiewicz, Richard M. Salzillo, Heather Ann Terry
  • Patent number: 7452186
    Abstract: The present invention provides an improved cooling circuit for a trailing edge of a turbine blade. The cooling circuit includes an inlet passage that receives a airflow and distributes the airflow through a feed passage. The feed passage primarily includes trip strips, at least one barrier including cross-over holes, teardrop shaped protrusions, and pockets disposed along a trailing edge. The geometry and positioning of both the cross-over holes and teardrop shaped protrusions downstream of the cross-over holes have been optimized to maximize cooling efficiency and reduce airflow. An improved transition between the inlet passage and the feed passage is also provided, which is arcuate and allows the airflow to maintain attachment and flow unimpeded from the inlet passage to the feed passage. The geometry of the pockets disposed along the trailing edge is optimized to improve cooling.
    Type: Grant
    Filed: August 16, 2005
    Date of Patent: November 18, 2008
    Assignee: United Technologies Corporation
    Inventors: Robert A. Charbonneau, Kenneth P. Botticello, Shawn J. Gregg, Kirk David Hlavaty, Jeffrey R. Levine, Kenneth A. Lonczak, Craig R. McGarrah, Dominic J. Mongillo, Lisa P. O'Neill, Edward Pietraszkiewicz, Richard M. Salzillo, Heather Ann Terry
  • Publication number: 20080211192
    Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.
    Type: Application
    Filed: March 1, 2007
    Publication date: September 4, 2008
    Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter