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).
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Patent number: 11493205Abstract: A combustor liner for a gas turbine engine includes at least one liner segment that has an external wall dimensioned to bound a combustion chamber. The external wall extends between leading and trailing edges in an axial direction and extends between opposed mate faces in a circumferential direction. A cooling circuit is defined by the external wall. A plurality of heat transfer features are distributed in the cooling circuit to define first and second prioritized flow regions on opposed sides of a first restricted flow region.Type: GrantFiled: August 30, 2021Date of Patent: November 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Laengheng Khoun, Edward F. Pietraszkiewicz, Joshua E. Kinnaman
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Publication number: 20210388988Abstract: A combustor liner for a gas turbine engine includes at least one liner segment that has an external wall dimensioned to bound a combustion chamber. The external wall extends between leading and trailing edges in an axial direction and extends between opposed mate faces in a circumferential direction. A cooling circuit is defined by the external wall. A plurality of heat transfer features are distributed in the cooling circuit to define first and second prioritized flow regions on opposed sides of a first restricted flow region.Type: ApplicationFiled: August 30, 2021Publication date: December 16, 2021Inventors: Laengheng Khoun, Edward F. Pietraszkiewicz, Joshua E. Kinnaman
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Patent number: 11156098Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a radial direction from a platform, the airfoil section extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and the airfoil section extending in the circumferential direction between pressure and suction sides. The platform extends in the axial direction between a platform leading edge and a platform trailing edge, and extends in the circumferential direction between a first mate face and a second mate face. The platform has a radially facing surface joined with the airfoil section and has a cold side surface opposed to the radially facing surface. A first thickness is defined between the radially facing surface and the cold side surface adjacent the first mate face, and a second thickness is defined between the radially facing surface and the cold side surface adjacent the second mate face.Type: GrantFiled: February 7, 2019Date of Patent: October 26, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Laengheng Khoun, Edward F. Pietraszkiewicz, David J. Hiskes
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Patent number: 11149548Abstract: A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed.Type: GrantFiled: October 24, 2014Date of Patent: October 19, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: James M. Koonankeil, Edward F Pietraszkiewicz, Francis M Tamiso, Kirk D Hlavaty
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Patent number: 11125434Abstract: A combustor liner for a gas turbine engine according to an example of the present disclosure includes, among other things, at least one liner segment that has an external wall dimensioned to bound a combustion chamber. The external wall extends between leading and trailing edges in an axial direction and extends between opposed mate faces in a circumferential direction. A cooling circuit is defined by the external wall. A plurality of heat transfer features are distributed in the cooling circuit to define a first restricted flow region that tapers from the leading edge to the trailing edge and to define at least one prioritized flow region that extends substantially from the leading edge to the trailing edge such that the at least one prioritized flow region is bounded by a perimeter of the first restricted flow region, and the at least one prioritized flow region has a lesser concentration of the plurality of heat transfer features than the first restricted flow region.Type: GrantFiled: December 10, 2018Date of Patent: September 21, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Laengheng Khoun, Edward F. Pietraszkiewicz, Joshua E. Kinnaman
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Publication number: 20200256195Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a radial direction from a platform, the airfoil section extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and the airfoil section extending in the circumferential direction between pressure and suction sides. The platform extends in the axial direction between a platform leading edge and a platform trailing edge, and extends in the circumferential direction between a first mate face and a second mate face. The platform has a radially facing surface joined with the airfoil section and has a cold side surface opposed to the radially facing surface. A first thickness is defined between the radially facing surface and the cold side surface adjacent the first mate face, and a second thickness is defined between the radially facing surface and the cold side surface adjacent the second mate face.Type: ApplicationFiled: February 7, 2019Publication date: August 13, 2020Inventors: Laengheng Khoun, Edward F. Pietraszkiewicz, David J. Hiskes
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Publication number: 20200182464Abstract: A combustor liner for a gas turbine engine according to an example of the present disclosure includes, among other things, at least one liner segment that has an external wall dimensioned to bound a combustion chamber. The external wall extends between leading and trailing edges in an axial direction and extends between opposed mate faces in a circumferential direction. A cooling circuit is defined by the external wall. A plurality of heat transfer features are distributed in the cooling circuit to define a first restricted flow region that tapers from the leading edge to the trailing edge and to define at least one prioritized flow region that extends substantially from the leading edge to the trailing edge such that the at least one prioritized flow region is bounded by a perimeter of the first restricted flow region, and the at least one prioritized flow region has a lesser concentration of the plurality of heat transfer features than the first restricted flow region.Type: ApplicationFiled: December 10, 2018Publication date: June 11, 2020Inventors: Laengheng Khoun, Edward F. Pietraszkiewicz, Joshua E. Kinnaman
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Patent number: 10677070Abstract: 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: GrantFiled: October 19, 2015Date of Patent: June 9, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Joseph F. Englehart, Edward F. Pietraszkiewicz, Wieslaw A. Chlus, David M. Konopka, Luke A. Hmiel, Kenneth Boucher
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Patent number: 10626729Abstract: An airfoil includes a cooling air passage for receiving a cooling air flow. A chevron including a first rib and a second rib extends from a common tip is disposed within the cooling passage for generating a turbulent flow to improve heat transfer. The chevron includes an angle between the first rib and the second rib that is greater than 90 degrees.Type: GrantFiled: March 13, 2014Date of Patent: April 21, 2020Assignee: United Technologies CorporationInventors: Seth J. Thomen, Edward F. Pietraszkiewicz, Dominic J. Mongillo, Jr., Wieslaw A. Chlus, Erik R. Granstrand
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Patent number: 10612388Abstract: An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit.Type: GrantFiled: August 27, 2015Date of Patent: April 7, 2020Assignee: United Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Rafael A. Perez, Edward F. Pietraszkiewicz
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Patent number: 10526912Abstract: A method of designing a turbine blade includes the steps of forming at least two notches on a tip of a turbine blade, each of the at least two notches having a known dimension. The turbine blade has a pressure side and a suction side. The method further includes the step of operating a gas turbine engine including the turbine blade to expand a length of the turbine blade such that the tip of the turbine engages a casing. The method further includes the steps of viewing the tip of the turbine blade after the step of operating of the gas turbine engine, determining an appearance of the notches on the tip and determining a manufacturing length of the turbine blade based on the step of determining the appearance the notches.Type: GrantFiled: April 21, 2016Date of Patent: January 7, 2020Assignee: United Technologies CorporationInventors: Stanley J. Funk, Edward F. Pietraszkiewicz
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Patent number: 10519802Abstract: 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: GrantFiled: April 26, 2017Date of Patent: December 31, 2019Assignee: United Technologies CorporationInventors: Thomas N. Slavens, Edward F. Pietraszkiewicz, Thomas J. Martin, Mark F. Zelesky, Steven B. Gautschi, Matthew A. Devore, Alexander Staroselsky
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Patent number: 10392958Abstract: 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: GrantFiled: May 26, 2015Date of Patent: August 27, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sergey Mironets, Edward F. Pietraszkiewicz, Alexander Staroselsky, Mark F. Zelesky
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Patent number: 10273808Abstract: 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: GrantFiled: November 11, 2015Date of Patent: April 30, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Dominic J. Mongillo, Edward F. Pietraszkiewicz
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Patent number: 10215031Abstract: 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: GrantFiled: March 12, 2014Date of Patent: February 26, 2019Assignee: United Technologies CorporationInventors: Jaime G. Ghigliotty, Edward F. Pietraszkiewicz, Dominic J. Mongillo, Jr., Christopher Corcoran
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Patent number: 10156157Abstract: 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: GrantFiled: February 13, 2015Date of Patent: December 18, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Christopher King, Edward F. Pietraszkiewicz
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Patent number: 10054055Abstract: 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: GrantFiled: November 19, 2015Date of Patent: August 21, 2018Assignee: United Technology CorporationInventors: Brandon W. Spangler, Edward F. Pietraszkiewicz
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Patent number: 9995173Abstract: 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: GrantFiled: October 27, 2015Date of Patent: June 12, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Pedro L. Castaneda, Edward F. Pietraszkiewicz, Rafael A. Perez, Nestor A. Alvarez, Seth J. Thomen
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Patent number: 9970319Abstract: 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: GrantFiled: May 4, 2015Date of Patent: May 15, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: James M. Koonankeil, Edward F. Pietraszkiewicz
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Patent number: 9963975Abstract: 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: GrantFiled: February 9, 2015Date of Patent: May 8, 2018Assignee: United Technologies CorporationInventors: Christopher King, Edward F. Pietraszkiewicz