Patents by Inventor Kevin E. Green
Kevin E. Green 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: 9441836Abstract: A fuel-air premixer for a combustor of a gas turbine engine includes a central passage disposed along an axis and operable to communicate a first airflow and an outer annular passage about the axis operable to communicate a second airflow. The fuel-air premixer further includes an inner annular passage about the axis and between the central passage and the outer annular passage for communicating fuel flow. The inner annular passage including an inner exit angled for directing fuel flow toward the axis into a mixer passage downstream of the outer and inner exits for mixing the fuel flow with the first and second airflows.Type: GrantFiled: July 10, 2012Date of Patent: September 13, 2016Assignee: United Technologies CorporationInventors: Jeffrey M. Cohen, Zhongtao Dai, Kevin E. Green
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Patent number: 8801372Abstract: A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge.Type: GrantFiled: November 5, 2012Date of Patent: August 12, 2014Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
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Patent number: 8784052Abstract: An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed.Type: GrantFiled: May 10, 2010Date of Patent: July 22, 2014Assignee: Hamilton Sundstrand CorporationInventors: Jun Shi, Kevin E. Green
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Publication number: 20140013763Abstract: A fuel-air premixer for a combustor of a gas turbine engine includes a central passage disposed along an axis and operable to communicate a first airflow and an outer annular passage about the axis operable to communicate a second airflow. The fuel-air premixer further includes an inner annular passage about the axis and between the central passage and the outer annular passage for communicating fuel flow. The inner annular passage including an inner exit angled for directing fuel flow toward the axis into a mixer passage downstream of the outer and inner exits for mixing the fuel flow with the first and second airflows.Type: ApplicationFiled: July 10, 2012Publication date: January 16, 2014Inventors: Jeffrey M. Cohen, Zhongtao Dai, Kevin E. Green
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Publication number: 20130232978Abstract: A fuel-air premixer for a combustor of a turbine engine includes a central passage along an axis. The central passage is operable to communicate an unswirled airflow. An outer annular passage is located around the axis and includes a multiple of first swirl vanes that are operable to communicate a first swirled airflow in a first direction. An inner annular passage is located around the axis between the central passage and the outer annular passage. The inner annular passage includes a multiple of second swirl vanes that are operable to communicate a second swirled airflow in a second direction different than the first direction.Type: ApplicationFiled: March 12, 2012Publication date: September 12, 2013Inventors: Zhongtao Dai, Jeffrey M. Cohen, Kevin E. Green
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Patent number: 8511975Abstract: A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud.Type: GrantFiled: July 5, 2011Date of Patent: August 20, 2013Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Paul F. Croteau
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Publication number: 20130008176Abstract: A system for supporting a shroud used in an engine has a shroud positioned radially outboard of a rotor, which shroud has a plurality of circumferentially spaced slots; a forward support ring for supporting the shroud; the forward support ring having a plurality of spaced apart first tabs on a first side for functioning as anti-rotation devices; the forward support ring having a plurality of spaced apart second tabs on a second side; and the second tabs engaging the slots in the shroud and circumferentially supporting the shroud.Type: ApplicationFiled: July 5, 2011Publication date: January 10, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jun Shi, Kevin E. Green, Paul F. Croteau
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Publication number: 20130011248Abstract: A shroud for use in a gas turbine engine has a ring with a plurality of protrusions and a plurality of slots and each of the protrusions having an arc length and parallel sides.Type: ApplicationFiled: July 5, 2011Publication date: January 10, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Paul F. Croteau, Kevin E. Green, Jun Shi
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Patent number: 8328505Abstract: A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.Type: GrantFiled: November 30, 2011Date of Patent: December 11, 2012Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
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Patent number: 8167546Abstract: A turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward edge of the forward metallic support ring configured to engage a turbine support case, and a plurality of tabs attached to an aft edge of the forward metallic support ring received by the slots of the ceramic shroud ring. Only two axially extending radial surfaces of each of the tabs attached to the aft edge of the forward metallic support ring are configured to contact the slots of the ceramic shroud ring.Type: GrantFiled: September 1, 2009Date of Patent: May 1, 2012Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Gregory E. Reinhardt
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Publication number: 20120070276Abstract: A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.Type: ApplicationFiled: November 30, 2011Publication date: March 22, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
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Patent number: 8092160Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.Type: GrantFiled: November 12, 2009Date of Patent: January 10, 2012Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
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Publication number: 20110274538Abstract: An example gas turbine engine shroud includes a first annular ceramic wall having an inner side for resisting high temperature turbine engine gasses and an outer side with a plurality of radial slots. A second annular metallic wall is positioned radially outwardly of and enclosing the first annular ceramic wall and has a plurality of tabs in communication with the slot of the first annular ceramic wall. The tabs of the second annular metallic wall and slots of the first annular ceramic wall are in communication such that the first annular ceramic wall and second annular metallic wall are affixed.Type: ApplicationFiled: May 10, 2010Publication date: November 10, 2011Inventors: Jun Shi, Kevin E. Green
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Publication number: 20110052384Abstract: A turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward edge of the forward metallic support ring configured to engage a turbine support case, and a plurality of tabs attached to an aft edge of the forward metallic support ring received by the slots of the ceramic shroud ring. Only two axially extending radial surfaces of each of the tabs attached to the aft edge of the forward metallic support ring are configured to contact the slots of the ceramic shroud ring.Type: ApplicationFiled: September 1, 2009Publication date: March 3, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jun Shi, Kevin E. Green, Gregory E. Reinhardt
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Patent number: 7771160Abstract: A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring.Type: GrantFiled: August 10, 2006Date of Patent: August 10, 2010Assignee: United Technologies CorporationInventors: Jun Shi, Shaoluo L. Butler, Kevin E. Green
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Patent number: 7762768Abstract: An assembly for mounting a ceramic turbine vane ring onto a turbine support casing comprises a first metal clamping ring and a second metal clamping ring. The first metal clamping ring is configured to engage with a first side of a tab member of the ceramic turbine vane ring. The second metal clamping ring is configured to engage with a second side of the tab member such that the tab member is disposed between the first and second metal clamping rings.Type: GrantFiled: November 13, 2006Date of Patent: July 27, 2010Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Daniel A. Mosher, John E. Holowczak, Gregory E. Reinhardt
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Publication number: 20100170264Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.Type: ApplicationFiled: November 12, 2009Publication date: July 8, 2010Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
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Publication number: 20100104433Abstract: A ceramic shroud assembly suitable for use in a gas turbine engine comprises a metal clamp ring shrink fitted around a ceramic shroud ring and an insulating and compliant interlayer. The interlayer is positioned between the metal clamp ring and the ceramic shroud ring.Type: ApplicationFiled: August 10, 2006Publication date: April 29, 2010Applicant: United Technologies Corporation One Financial PlazaInventors: Jun Shi, Shaoluo L. Butler, Kevin E. Green
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Patent number: 7665960Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.Type: GrantFiled: August 10, 2006Date of Patent: February 23, 2010Assignee: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
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Publication number: 20090272122Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.Type: ApplicationFiled: August 10, 2006Publication date: November 5, 2009Applicant: United Technologies CorporationInventors: Jun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn Levasseur