Patents by Inventor Ed Zurmehly
Ed Zurmehly 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: 20190022781Abstract: Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.Type: ApplicationFiled: November 14, 2017Publication date: January 24, 2019Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bradley Reed Tucker, Ardeshir Riahi, Jason Smoke, Ed Zurmehly
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Patent number: 10030542Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud.Type: GrantFiled: October 2, 2015Date of Patent: July 24, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Ed Zurmehly, David R. Waldman, Deanna Pinar Chase, David K Jan, Gregory Ockenfels, Alonso Peralta-Duran
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Patent number: 9844826Abstract: Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.Type: GrantFiled: July 25, 2014Date of Patent: December 19, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Bradley Reed Tucker, Ardeshir Riahi, Jason Smoke, Ed Zurmehly
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Patent number: 9657642Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.Type: GrantFiled: March 27, 2014Date of Patent: May 23, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shezan Kanjiyani, John Gintert, Rajiv Rana, Lorenzo Crosatti, Bradley Reed Tucker, Ed Zurmehly
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Patent number: 9644495Abstract: Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.Type: GrantFiled: August 20, 2013Date of Patent: May 9, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Ed Zurmehly, Cristopher Frost, Michael O'Brien, Donald G Godfrey
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Publication number: 20170096911Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel.Type: ApplicationFiled: October 2, 2015Publication date: April 6, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Ed Zurmehly, David R. Waldman, Deanna Pinar Chase, David K. Jan, Greg Ockenfels, Alonso Peralta-Duran
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Patent number: 9506365Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.Type: GrantFiled: April 21, 2014Date of Patent: November 29, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Ardeshir Riahi, Ed Zurmehly, Alexander MirzaMoghadam
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Publication number: 20160024948Abstract: Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.Type: ApplicationFiled: July 25, 2014Publication date: January 28, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Bradley Reed Tucker, Ardeshir Riahi, Jason Smoke, Ed Zurmehly
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Publication number: 20150300192Abstract: Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.Type: ApplicationFiled: April 21, 2014Publication date: October 22, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Ardeshir Riahi, Ed Zurmehly, Alexander MirzaMoghadam
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Publication number: 20150275763Abstract: A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.Type: ApplicationFiled: March 27, 2014Publication date: October 1, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Shezan Kanjiyani, John Gintert, Rajiv Rana, Lorenzo Crosatti, Bradley Reed Tucker, Ed Zurmehly
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Publication number: 20150052872Abstract: Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.Type: ApplicationFiled: August 20, 2013Publication date: February 26, 2015Inventors: Ed Zurmehly, Cristopher Frost, Michael O'Brien, Donald G Godfrey