Patents by Inventor Edward F. Pietraszkiewicz

Edward F. Pietraszkiewicz 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: 10392958
    Abstract: A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: August 27, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergey Mironets, Edward F. Pietraszkiewicz, Alexander Staroselsky, Mark F. Zelesky
  • Patent number: 10273808
    Abstract: An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.
    Type: Grant
    Filed: November 11, 2015
    Date of Patent: April 30, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Dominic J. Mongillo, Edward F. Pietraszkiewicz
  • Patent number: 10215031
    Abstract: A gas turbine engine component includes first and second walls spaced apart from one another to provide a cooling passage. First and second trip strips are respectively provided on the first and second walls and arranged to face one another. The first and second trip strips are arranged in an interleaved fashion with respect to one another in a direction.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: February 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Jaime G. Ghigliotty, Edward F. Pietraszkiewicz, Dominic J. Mongillo, Jr., Christopher Corcoran
  • Patent number: 10156157
    Abstract: A component for a gas turbine engine is provided. The component includes an internal cooling passage disposed within the component, and an s-shaped trip strip formed on a surface of the internal cooling passage.
    Type: Grant
    Filed: February 13, 2015
    Date of Patent: December 18, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher King, Edward F. Pietraszkiewicz
  • Patent number: 10054055
    Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling passage and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling passage forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the channel and the cooling passage so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.
    Type: Grant
    Filed: November 19, 2015
    Date of Patent: August 21, 2018
    Assignee: United Technology Corporation
    Inventors: Brandon W. Spangler, Edward F. Pietraszkiewicz
  • Patent number: 9995173
    Abstract: The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: June 12, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Pedro L. Castaneda, Edward F. Pietraszkiewicz, Rafael A. Perez, Nestor A. Alvarez, Seth J. Thomen
  • Patent number: 9970319
    Abstract: An airfoil body includes an airfoil wall defined between an internal cavity surface and an external airfoil surface. A pad extends from the internal cavity surface. A cooling hole extends from the external airfoil surface, through the airfoil wall and through the pad for fluid communication through the airfoil wall.
    Type: Grant
    Filed: May 4, 2015
    Date of Patent: May 15, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James M. Koonankeil, Edward F. Pietraszkiewicz
  • Patent number: 9963975
    Abstract: A structure for creating a core for a gas turbine engine component comprises a body with a curved surface defining a turn passage. A plurality of protrusions are formed within a wall surface of the turn passage. A plurality of protrusions are configured to extend transversely relative to the curved surface. A gas turbine engine component is also disclosed.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: May 8, 2018
    Assignee: United Technologies Corporation
    Inventors: Christopher King, Edward F. Pietraszkiewicz
  • Patent number: 9932837
    Abstract: A rotor blade comprises a root section, an airfoil section, a leading edge cooling cavity, an intermediate cooling cavity, and a trailing edge cooling cavity. The leading edge, intermediate, and trailing edge cooling cavities each extend spanwise through the airfoil section from a coolant inlet passage in the root section, and each terminate proximate the airfoil tip.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: April 3, 2018
    Assignee: United Technologies Corporation
    Inventors: Christopher Corcoran, Jamie G. Ghigliotty, Rafael A. Perez, Edward F. Pietraszkiewicz
  • Patent number: 9835033
    Abstract: A hybrid airfoil according to an exemplary aspect of the present disclosure includes, among other things, a leading edge portion made of a first material, a trailing edge portion made of a second material, and an intermediate portion between the leading edge portion and the trailing edge portion made of a non-metallic material. A rib is disposed between the leading edge portion and the intermediate portion. A protrusion of one of the rib and the intermediate portion is received within a pocket of the other of the rib and the intermediate portion.
    Type: Grant
    Filed: March 17, 2015
    Date of Patent: December 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergey Mironets, Edward F. Pietraszkiewicz, Alexander Staroselsky, Mark F. Zelesky
  • Publication number: 20170226893
    Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.
    Type: Application
    Filed: April 26, 2017
    Publication date: August 10, 2017
    Inventors: Thomas N. Slavens, Edward F. Pietraszkiewicz, Thomas J. Martin, Mark F. Zelesky, Steven B. Gautschi, Matthew A. Devore, Alexander Staroselsky
  • Patent number: 9670797
    Abstract: A vane structure includes a baffle movably mounted within an aperture, the baffle movable to control a cooling flow between a first cooling cavity and a second cooling cavity.
    Type: Grant
    Filed: September 28, 2012
    Date of Patent: June 6, 2017
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Edward F. Pietraszkiewicz, Thomas J. Martin, Mark F. Zelesky, Steven B. Gautschi, Matthew A. Devore, Alexander Staroselsky
  • Publication number: 20170145923
    Abstract: A platform is disclosed. The platform may include an airfoil section with a cooling passage and a platform. The platform may have various cooling features, such as a platform cooling apparatus. The platform cooling apparatus may have a cooling passage forming a channel disposed at least partially through the platform and the platform cooling apparatus may have an inflow channel in fluidic communication with the channel and the cooling passage so that cooling air may travel from the cooling cavity of the blade airfoil section and into the platform cooling apparatus. Moreover, the platform cooling apparatus may have a cooling cover apparatus at least partially fluidically sealing the platform cooling apparatus.
    Type: Application
    Filed: November 19, 2015
    Publication date: May 25, 2017
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Edward F. Pietraszkiewicz
  • Publication number: 20170130590
    Abstract: An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.
    Type: Application
    Filed: November 11, 2015
    Publication date: May 11, 2017
    Inventors: Brandon W. Spangler, Dominic J. Mongillo, Edward F. Pietraszkiewicz
  • Publication number: 20170107830
    Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.
    Type: Application
    Filed: October 19, 2015
    Publication date: April 20, 2017
    Inventors: Joseph F. Englehart, Edward F. Pietraszkiewicz, Wieslaw A. Chlus, David M. Konopka, Luke A. Hmiel, Kenneth Boucher
  • Patent number: 9561555
    Abstract: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.
    Type: Grant
    Filed: December 28, 2012
    Date of Patent: February 7, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James M. Koonankeil, Edward F. Pietraszkiewicz, Karl A. Schachtner, Kevin J. Klinefelter, Markus W. Fritch, Jason Daley
  • Publication number: 20170022823
    Abstract: A turbine blade is provided. The turbine blade includes a suction side wall including a first tip edge, a pressure side wall opposite the suction side wall and including a second tip edge. A tip wall extends between the suction side wall and the pressure side wall. The tip wall is recessed from the first tip edge and the second tip edge to define a tip pocket having a suction side wall tip section and a pressure side wall tip section. At least one turbulator is formed in the tip pocket on at least one of the following: the tip wall, the suction side wall tip section, and the pressure side wall tip section. The at least one turbulator formed on the tip wall is selectively positioned.
    Type: Application
    Filed: July 23, 2015
    Publication date: January 26, 2017
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: EDWARD F. PIETRASZKIEWICZ, BRANDON W. SPANGLER
  • Patent number: 9476308
    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.
    Type: Grant
    Filed: December 27, 2012
    Date of Patent: October 25, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Travis Goeller, Erik R. Granstrand, Irwin D. Singer, Dominic J. Mongillo, Jr., Edward F. Pietraszkiewicz
  • Publication number: 20160237849
    Abstract: A component for a gas turbine engine is provided. The component includes an internal cooling passage disposed within the component, and an s-shaped trip strip formed on a surface of the internal cooling passage.
    Type: Application
    Filed: February 13, 2015
    Publication date: August 18, 2016
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher King, Edward F. Pietraszkiewicz
  • Publication number: 20160230563
    Abstract: A. structure for creating a core for a gas turbine engine component comprises a body with a curved surface defining a turn passage. A plurality of protrusions are formed within a wall surface of the turn passage. A plurality of protrusions are configured to extend transversely relative to the curved surface. A gas turbine engine component is also disclosed.
    Type: Application
    Filed: February 9, 2015
    Publication date: August 11, 2016
    Inventors: Christopher King, Edward F. Pietraszkiewicz