Patents by Inventor Jeffrey R. Levine
Jeffrey R. Levine 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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Publication number: 20240123449Abstract: A system and associated method for concentrating and separating components of different densities from fluid containing cells using a centrifuge includes a container defining a cavity for receiving the fluid. The container has a top, a sidewall extending from the top, and a bottom disposed opposite the top and in sealing engagement with the sidewall. An insert is slidably disposed in the cavity of the container and defines a lumen through the insert. The lumen, which includes a hole and a funnel-shaped upper portion in fluid communication with the hole, forms an open fluid path between opposite ends of the insert. The insert has a density such that upon centrifugation a selected component of the fluid resides within the lumen. A container port is disposed in the top of the container to transfer the fluid into the container and to withdraw a fluid component other than the selected component from the container.Type: ApplicationFiled: May 18, 2023Publication date: April 18, 2024Inventors: Andy H. Levine, John C. Meade, Neil Tischler, Jeffrey R. Chabot, Andrew McGillicuddy, Neil F. Duffy, JR.
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Patent number: 10808546Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: GrantFiled: March 27, 2019Date of Patent: October 20, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Patent number: 10428666Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.Type: GrantFiled: December 12, 2016Date of Patent: October 1, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John David Forbes, Gregory Anselmi, Christina E. Botnick, Eleanor D. Kaufman, Jeffrey Leon, Jeffrey R. Levine, Gerald M. Mace, Daniel C. Nadeau, Tania Bhatia Kashyap, Richard N. Allen
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Publication number: 20190218916Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: ApplicationFiled: March 27, 2019Publication date: July 18, 2019Inventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Patent number: 10294806Abstract: An article includes a body that has a coating thereon. The coating has a first portion disposed on a first section of the body and a second portion disposed on a second, different section of the body. The first portion has a first microstructure and the second portion has a second, different microstructure.Type: GrantFiled: March 11, 2014Date of Patent: May 21, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sarah Riley, Jeffrey R. Levine, Mark A. Boeke
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Patent number: 10253634Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: GrantFiled: April 25, 2014Date of Patent: April 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Patent number: 10253635Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.Type: GrantFiled: April 30, 2018Date of Patent: April 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Dominic J. Mongillo, Jr., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Patent number: 10132168Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.Type: GrantFiled: March 14, 2016Date of Patent: November 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey Leon, Daniel C. Nadeau, Jeffrey R. Levine, Eleanor D. Kaufman, Richard N. Allen, Evan P. Molony, Gregory Anselmi
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Patent number: 10119407Abstract: A turbine engine component has an airfoil portion having a pressure side, a suction side, and a trailing edge. The trailing edge has a center discharge cooling circuit, which center discharge cooling circuit has an exit defined by a concave surface on the pressure side of the airfoil portion and a convex surface on the suction side of the airfoil portion. The airfoil portion has a thermal barrier coating on the pressure side and the suction side. The thermal barrier coating on the convex surface tapers to zero in thickness at a point spaced from the trailing edge so as to leave an uncoated portion on the convex surface.Type: GrantFiled: December 30, 2013Date of Patent: November 6, 2018Assignee: United Technologies CorporationInventor: Jeffrey R Levine
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Publication number: 20180245470Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform extending from a root section, an airfoil section extending radially from the platform to an airfoil tip, a plurality of cooling passages defined in an external wall of the airfoil tip, the plurality of cooling passages extending radially between the airfoil tip and a cavity in the airfoil section bounded by the external wall, and each of the plurality of cooling passages defining an inlet port along the cavity and an exit port adjacent the airfoil tip, and at least one internal feature within each of the plurality of cooling passages that meter flow to the respective exit port.Type: ApplicationFiled: April 30, 2018Publication date: August 30, 2018Inventors: Dominic J. Mongillo, JR., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Publication number: 20180163551Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.Type: ApplicationFiled: December 12, 2016Publication date: June 14, 2018Inventors: John David Forbes, Gregory Anselmi, Christina E. Botnick, Eleanor D. Kaufman, Jeffrey Leon, Jeffrey R. Levine, Gerald M. Mace, Daniel C. Nadeau, Tania Bhatia Kashyap, Richard N. Allen
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Patent number: 9995147Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.Type: GrantFiled: February 11, 2015Date of Patent: June 12, 2018Assignee: United Technologies CorporationInventors: Dominic J. Mongillo, Jr., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Patent number: 9982560Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.Type: GrantFiled: January 16, 2015Date of Patent: May 29, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark A. Boeke, Kristopher K. Anderson, Jeffrey J. De Gray, Jeffrey R. Levine, Sarah Riley, Richard M. Salzillo, Jr.
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Patent number: 9938837Abstract: An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.Type: GrantFiled: March 12, 2013Date of Patent: April 10, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey R. Levine, Jeffrey S. Beattie, Malcolm C. Staddon
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Publication number: 20170260864Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.Type: ApplicationFiled: March 14, 2016Publication date: September 14, 2017Applicant: United Technologies CorporationInventors: Jeffrey Leon, Daniel C. Nadeau, Jeffrey R. Levine, Eleanor D. Kaufman, Richard N. Allen, Evan P. Molony, Gregory Anselmi
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Publication number: 20170198601Abstract: A gas turbine engine component comprising a nozzle segment, the nozzle segment comprising at least one substrate having a surface. A metallic bondcoat is coupled to the surface of the substrate. An yttria-stabilized zirconia thermal barrier coating is coupled to the metallic bondcoat opposite the surface.Type: ApplicationFiled: January 12, 2016Publication date: July 13, 2017Inventors: Michael N. Task, Mark A. Boeke, Jeffrey R. Levine, Russell J. Bergman
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Publication number: 20160230564Abstract: A turbine blade according to an example of the present disclosure includes, among other things, a platform, an airfoil tip, and an airfoil section between the platform and the airfoil tip. The airfoil section has a cavity spaced radially from the airfoil tip and a plurality of cooling passages radially between the cavity and the airfoil tip. Each of the plurality of cooling passages defines an exit port adjacent the airfoil tip. An internal feature within each of the plurality of cooling passages is configured to meter flow to the exit port.Type: ApplicationFiled: February 11, 2015Publication date: August 11, 2016Inventors: Dominic J. Mongillo, JR., Jeffrey R. Levine, Kyle C. Lana, Sasha M. Moore
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Publication number: 20160208627Abstract: An airfoil platform includes a platform body having an arcuate base defining a centerline axis. A rail extends radially outboard from a side of the arcuate base. A feed orifice is defined at least partially in the rail. The inner diameter edge of an axially facing opening of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body and forming the feed orifice through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.Type: ApplicationFiled: January 16, 2015Publication date: July 21, 2016Inventors: Mark A. Boeke, Kristopher K. Anderson, Jeffrey J. De Gray, Jeffrey R. Levine, Sarah Riley, Richard M. Salzillo, JR.
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Publication number: 20160090846Abstract: An airfoil for a gas turbine engine includes an outer airfoil wall that provides an exterior surface and multiple radially extending cooling passages. The exterior surface provides pressure and suctions sides joined by leading and trailing edges. The cooling passages include a supply passage arranged upstream from and in fluid communication with a trailing edge passage. A cooling hole extends through the outer airfoil wall from the supply passage to the exterior surface on the suction side.Type: ApplicationFiled: April 25, 2014Publication date: March 31, 2016Inventors: Sarah Riley, Sasha M. Moore, Jeffrey R. Levine
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Patent number: 9279331Abstract: An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.Type: GrantFiled: April 23, 2012Date of Patent: March 8, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey R. Levine, Jeffrey S. Beattie