Patents by Inventor Kevin Seymour
Kevin Seymour 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: 11111807Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.Type: GrantFiled: December 17, 2019Date of Patent: September 7, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Kevin Seymour, Christopher W. Strock
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Patent number: 11073028Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material and a thermal barrier coating material applied over said film of oxidant resistant coating.Type: GrantFiled: July 19, 2018Date of Patent: July 27, 2021Assignee: Raytheon Technologies CorporationInventors: Christopher W. Strock, Kevin Seymour
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Patent number: 11028721Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degree Fahrenheit, comprising: a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.Type: GrantFiled: July 19, 2018Date of Patent: June 8, 2021Assignee: Ratheon Technologies CorporationInventors: Kevin Seymour, Christopher W. Strock, Thomas D. Kasprow
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Patent number: 10927685Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.Type: GrantFiled: July 19, 2018Date of Patent: February 23, 2021Assignee: Raytheon Technologies CorporationInventors: Kevin Seymour, Christopher W. Strock, Thomas D. Kasprow
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Patent number: 10794221Abstract: A gas turbine engine includes a rotatable component and a non-rotatable component. A seal is carried on one of the rotatable component or the non-rotatable component to provide sealing there between. The seal includes a geopolymer seal element.Type: GrantFiled: April 25, 2017Date of Patent: October 6, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Kevin Seymour, Christopher W. Strock
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Patent number: 10731260Abstract: A gas turbine engine includes a rotor that has a rim, blades extending radially outwards from the rim, a hub extending radially inwards from the rim, an arm extending axially from the rim, the arm having a radially outer surface, and a coating disposed on the radially outer surface. The coating is zirconia-toughened alumina in which the alumina is a matrix with grains of the zirconia dispersed there through. The grains of zirconia are predominantly a tetragonal crystal structure.Type: GrantFiled: June 12, 2017Date of Patent: August 4, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Kevin Seymour, Christopher W. Strock
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Publication number: 20200141260Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.Type: ApplicationFiled: December 17, 2019Publication date: May 7, 2020Inventors: Kevin Seymour, Christopher W. Strock
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Publication number: 20200095171Abstract: A method for coating a substrate with a ceramic coating, includes the steps of: applying a bond coat material to a surface of a substrate to form a bond coat on the surface; and applying a ceramic coat over the bond coat, wherein the step of applying the bond coat material produces a bond coat having a lower elastic modulus as compared to a conventionally applied bond coat.Type: ApplicationFiled: December 10, 2018Publication date: March 26, 2020Inventors: Christopher W. Strock, Kevin Seymour, Agnieszka M. Wusatowska-Sarnek, Sergei F. Burlatsky
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Publication number: 20200024975Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material and a thermal barrier coating material applied over said film of oxidant resistant coating.Type: ApplicationFiled: July 19, 2018Publication date: January 23, 2020Applicant: United Technologies CorporationInventors: Christopher W. Strock, Kevin Seymour
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Publication number: 20200024971Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 1750 degree Fahrenheit, comprising a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.Type: ApplicationFiled: July 19, 2018Publication date: January 23, 2020Applicant: United Technologies CorporationInventors: Kevin Seymour, Christopher W. Strock, Thomas D. Kasprow
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Publication number: 20200025016Abstract: An abrasive coating for a substrate of a component in a gas path exposed to a maximum temperature of 500 degree Fahrenheit, comprising: a plurality of grit particles adapted to be placed on a top surface of the substrate; a matrix material bonded to the top surface; the matrix material partially surrounds the grit particles, wherein the grit particles extend above the matrix material relative to the top surface; and a film of oxidant resistant coating applied over the plurality of grit particles and the matrix material.Type: ApplicationFiled: July 19, 2018Publication date: January 23, 2020Applicant: United Technologies CorporationInventors: Kevin Seymour, Christopher W. Strock, Thomas D. Kasprow
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Patent number: 10526908Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.Type: GrantFiled: April 25, 2017Date of Patent: January 7, 2020Assignee: United Technologies CorporationInventors: Kevin Seymour, Christopher W. Strock
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Publication number: 20190186281Abstract: An air seal in a gas turbine engine includes a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a lubricious oxide solid lubricant filler.Type: ApplicationFiled: December 20, 2017Publication date: June 20, 2019Applicant: United Technologies CorporationInventors: Pantcho Stoyanov, Christopher W. Strock, Kevin Seymour
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Publication number: 20180355489Abstract: A gas turbine engine includes a rotor that has a rim, blades extending radially outwards from the rim, a hub extending radially inwards from the rim, an arm extending axially from the rim, the arm having a radially outer surface, and a coating disposed on the radially outer surface. The coating is zirconia-toughened alumina in which the alumina is a matrix with grains of the zirconia dispersed there through. The grains of zirconia are predominantly a tetragonal crystal structure.Type: ApplicationFiled: June 12, 2017Publication date: December 13, 2018Inventors: Kevin Seymour, Christopher W. Strock
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Publication number: 20180306056Abstract: A gas turbine engine includes a rotatable component and a non-rotatable component. A seal is carried on one of the rotatable component or the non-rotatable component to provide sealing there between. The seal includes a geopolymer seal element.Type: ApplicationFiled: April 25, 2017Publication date: October 25, 2018Inventors: Kevin Seymour, Christopher W. Strock
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Publication number: 20180306047Abstract: A gas turbine engine includes a circumferential row of blades, with the blades having respective blade tips. A seal is disposed about the blades. The seal has an abradable layer which the tips of the blades, at times, rub against when the blades rotate. The rubbing produces a maximum temperature at the abradable layer. The abradable layer includes a metal matrix and microballoons dispersed in the metal matrix. The microballoons are formed of a glass that has a glass transition temperature that is approximately 50° F. to 300° F. greater than the maximum temperature.Type: ApplicationFiled: April 25, 2017Publication date: October 25, 2018Inventors: Kevin Seymour, Christopher W. Strock