Patents by Inventor Eleanor D. Kaufman
Eleanor D. Kaufman 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: 10968751Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a suction side of an airfoil of the turbine blade and in fluid communication with an internal cavity of the turbine blade; and wherein the at least some of the plurality of cooling holes are located in the airfoil according to the coordinates of Tables 1 and/or 2.Type: GrantFiled: September 14, 2018Date of Patent: April 6, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Rafael A. Perez, Eleanor D. Kaufman, Donald Kastel, Andres E. Diaz, Efrain E. Vega, Juan Pablo Lopez
-
Patent number: 10683760Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform.Type: GrantFiled: May 15, 2015Date of Patent: June 16, 2020Assignee: United Technologies CorporationInventors: Eleanor D. Kaufman, Matthew A. Devore
-
Publication number: 20200088041Abstract: Disclosed herein is a turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a suction side of an airfoil of the turbine blade and in fluid communication with an internal cavity of the turbine blade; and wherein the at least some of the plurality of cooling holes are located in the airfoil according to the coordinates of Tables 1 and/or 2.Type: ApplicationFiled: September 14, 2018Publication date: March 19, 2020Inventors: Rafael A. Perez, Eleanor D. Kaufman, Donald Kastel, Andres E. Diaz, Efrain E. Vega, Juan Pablo Lopez
-
Patent number: 10513932Abstract: A turbine engine airfoil includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.Type: GrantFiled: July 1, 2016Date of Patent: December 24, 2019Assignee: United Technologies CorporationInventors: Mark F. Zelesky, Eleanor D. Kaufman
-
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
-
Patent number: 10253636Abstract: A baffle insert for a component of a gas turbine engine is provided. The baffle insert having: a first fluid conduit having a first interior cavity extending therethrough; a second fluid conduit having a second interior cavity extending therethrough; and a member located between the first fluid conduit and the second fluid conduit, wherein the member fluidly couples the first interior cavity to an exterior of the second fluid conduit, and wherein the member fluidly couples the second interior cavity to an exterior of the first fluid conduit and wherein the first interior cavity is isolated from the second interior cavity.Type: GrantFiled: January 18, 2016Date of Patent: April 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew A. Devore, Eleanor D. Kaufman
-
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
-
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
-
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
-
Publication number: 20170204731Abstract: A baffle insert for a component of a gas turbine engine is provided. The baffle insert having: a first fluid conduit having a first interior cavity extending therethrough; a second fluid conduit having a second interior cavity extending therethrough; and a member located between the first fluid conduit and the second fluid conduit, wherein the member fluidly couples the first interior cavity to an exterior of the second fluid conduit, and wherein the member fluidly couples the second interior cavity to an exterior of the first fluid conduit and wherein the first interior cavity is isolated from the second interior cavity.Type: ApplicationFiled: January 18, 2016Publication date: July 20, 2017Inventors: Matthew A. Devore, Eleanor D. Kaufman
-
Publication number: 20160376895Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least the leading edge portion or the trailing edge portion of the outer surface of the platform.Type: ApplicationFiled: May 15, 2015Publication date: December 29, 2016Inventors: Eleanor D. KAUFMAN, Matthew A. DEVORE
-
Publication number: 20160333699Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.Type: ApplicationFiled: December 26, 2014Publication date: November 17, 2016Inventors: James B. Downey, JR., Brenda Zhang, Steven G. Lemieux, Eleanor D. Kaufman, Takao Fukuda, Daniel C. Nadeau
-
Publication number: 20160312623Abstract: A turbine engine airfoil includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.Type: ApplicationFiled: July 1, 2016Publication date: October 27, 2016Inventors: Mark F. Zelesky, Eleanor D. Kaufman
-
Patent number: 9163518Abstract: A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion.Type: GrantFiled: March 18, 2008Date of Patent: October 20, 2015Assignee: United Technologies CorporationInventors: Matthew A. Devore, Eleanor D. Kaufman
-
Publication number: 20130243575Abstract: A turbine engine component includes a first surface to be cooled by a flow of cooling air. The first surface includes a pedestal array and a first row of contour bumps. The pedestal array includes first and second rows of pedestals extending from the first surface. The second row of pedestals runs in a direction generally parallel to the first row of pedestals. The first row of contour bumps extends from the first surface between the first row of pedestals and the second row of pedestals and runs parallel to the first row of pedestals. The first row of contour bumps is aligned such that at least one of the contour bumps of the first row of contour bumps is positioned at least one of immediately downstream of a pedestal of the first row of pedestals and immediately upstream of a pedestal of the second row of pedestals.Type: ApplicationFiled: March 13, 2012Publication date: September 19, 2013Applicant: United Technologies CorporationInventors: Mark F. Zelesky, Eleanor D. Kaufman
-
Patent number: 8449254Abstract: An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.Type: GrantFiled: March 29, 2010Date of Patent: May 28, 2013Assignee: United Technologies CorporationInventors: Matthew A. Devore, Eleanor D. Kaufman
-
Publication number: 20110236178Abstract: An example airfoil cooling arrangement includes a airfoil wall having a first face and a second face opposite the first face. The airfoil wall establishes a channel that is configured to communicate fluid between an inlet aperture and an outlet aperture. The channel includes secondary portion that branch from a primary portion. An example airfoil cooling method includes receiving a flow of fluid from a airfoil core cavity and communicating the flow of fluid through channel within a wall of the airfoil. The channel has a secondary portion branching from a primary portion.Type: ApplicationFiled: March 29, 2010Publication date: September 29, 2011Inventors: Matthew A. Devore, Eleanor D. Kaufman
-
Patent number: 8016546Abstract: Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.Type: GrantFiled: July 24, 2007Date of Patent: September 13, 2011Assignee: United Technologies Corp.Inventors: Raymond Surace, Eleanor D. Kaufman, Andrew D. Milliken, William Abdel-Messeh
-
Publication number: 20100054915Abstract: An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.Type: ApplicationFiled: August 28, 2008Publication date: March 4, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew A. Devore, Eleanor D. Kaufman, Raymond Surace, William Abdel-Messeh
-
Publication number: 20090238695Abstract: A turbine engine component has an airfoil portion with a pressure side wall, a suction side wall, and a trailing edge. The turbine engine component further has at least one first cooling circuit core embedded within the pressure side wall, with each first cooling circuit core having a first exit for discharging a cooling fluid, at least one second cooling circuit core embedded within the suction side wall, with each second cooling circuit core having a second exit for discharging a cooling fluid, and the first and second exits being aligned in a spanwise direction of the airfoil portion.Type: ApplicationFiled: March 18, 2008Publication date: September 24, 2009Applicant: United Technologies CorporationInventors: Matthew A. Devore, Eleanor D. Kaufman