Patents by Inventor Kevin Zacchera
Kevin Zacchera 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: 11118480Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.Type: GrantFiled: December 4, 2017Date of Patent: September 14, 2021Assignee: Raytheon Technologies CorporationInventors: Jeffrey J. Lienau, Dustin W. Davis, Jonathan Lemoine, Kevin Zacchera
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Patent number: 11041391Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.Type: GrantFiled: April 20, 2020Date of Patent: June 22, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
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Patent number: 11015464Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: GrantFiled: January 24, 2020Date of Patent: May 25, 2021Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10871108Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.Type: GrantFiled: June 19, 2018Date of Patent: December 22, 2020Assignee: Raytheon Technologies CorporationInventors: Kevin Zacchera, Matthew Andrew Hough, Jonathan Lemoine, Christopher Treat, Alberto A. Mateo
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Publication number: 20200386106Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.Type: ApplicationFiled: April 20, 2020Publication date: December 10, 2020Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
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Combustor liner panel with a multiple of heat transfer augmentors for a gas turbine engine combustor
Patent number: 10830448Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.Type: GrantFiled: October 26, 2016Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: Monica Pacheco-Tougas, Kevin Zacchera, Jonathan Jeffery Eastwood -
Patent number: 10823410Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused edge blended into a hot side of the linear panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused edge blended into a hot side of the linear panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused edge blended into a hot side of a linear panel; and applying a thermal barrier coating to the hot side of the liner panel.Type: GrantFiled: October 26, 2016Date of Patent: November 3, 2020Assignee: Raytheon Technologies CorporationInventors: Jonathan Jeffery Eastwood, Kevin Zacchera, Brian T. Hazel, William F. Werkheiser
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Publication number: 20200277867Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: ApplicationFiled: January 24, 2020Publication date: September 3, 2020Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10738701Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.Type: GrantFiled: August 30, 2017Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10670269Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused gate blended into a hot side of the liner panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused gate blended into a hot side of the liner panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused gate tangentially cast into a hot side of a liner panel; and applying a thermal barrier coating to the hot side of the liner panel over the remnant of the radiused gate.Type: GrantFiled: October 26, 2016Date of Patent: June 2, 2020Assignee: Raytheon Technologies CorporationInventors: Jonathan Jeffery Eastwood, Kevin Zacchera, Brian T. Hazel, William F. Werkheiser
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Patent number: 10619857Abstract: A combustor panel may include an attachment feature having a central longitudinal axis and extending from a cold side of the combustor panel. The attachment feature may include a tip portion and a base portion and the attachment feature may be configured to extend through a combustor shell such that the tip portion is disposed outward of a diffuser-facing side of the combustor shell. The base portion may be configured to be disposed between the cold side of the combustor panel and the diffuser-facing side of the combustor shell. The attachment feature may define a core passage extending from an inlet opening defined on the tip portion and extending partially through the attachment feature to terminate within the attachment feature. The attachment feature may also define an offshoot passage extending from the core passage to an outlet opening defined on the base portion.Type: GrantFiled: September 8, 2017Date of Patent: April 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Lemoine, Steven D. Porter, Kevin Zacchera
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Patent number: 10584601Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: GrantFiled: August 30, 2017Date of Patent: March 10, 2020Assignee: United Technologies CorporationInventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10577971Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.Type: GrantFiled: November 8, 2017Date of Patent: March 3, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Joshua Daniel Winn, Anthony P. Cherolis, Steven D. Porter, Christopher Treat, Kevin Zacchera
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Publication number: 20190107059Abstract: A combustor cooling system for a combustor of a gas turbine engine is provided. The combustor cooling system comprising: a heat exchanger fluidly connected to a compressor section of the gas turbine engine, the heat exchanger being configured to receive compressor bleed air from the compressor section and cool the compressor bleed air; and a plenum assembly fluidly connected to the heat exchanger, the plenum assembly configured to receive cooled compressor bleed air from the heat exchanger and distribute the cooled compressor bleed air to one or more areas of the combustor.Type: ApplicationFiled: October 10, 2017Publication date: April 11, 2019Inventors: Kevin Zacchera, Jonathan Lemoine
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Publication number: 20190078789Abstract: A combustor panel may include an attachment feature having a central longitudinal axis and extending from a cold side of the combustor panel. The attachment feature may include a tip portion and a base portion and the attachment feature may be configured to extend through a combustor shell such that the tip portion is disposed outward of a diffuser-facing side of the combustor shell. The base portion may be configured to be disposed between the cold side of the combustor panel and the diffuser-facing side of the combustor shell. The attachment feature may define a core passage extending from an inlet opening defined on the tip portion and extending partially through the attachment feature to terminate within the attachment feature. The attachment feature may also define an offshoot passage extending from the core passage to an outlet opening defined on the base portion.Type: ApplicationFiled: September 8, 2017Publication date: March 14, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JONATHAN LEMOINE, STEVEN D. PORTER, KEVIN ZACCHERA
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Publication number: 20190063239Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Publication number: 20190063323Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.Type: ApplicationFiled: August 30, 2017Publication date: February 28, 2019Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
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Patent number: 10215098Abstract: A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.Type: GrantFiled: January 22, 2015Date of Patent: February 26, 2019Assignee: United Technologies CorporationInventors: Anthony P. Cherolis, Jorge I. Farah, Seth A. Max, John H. Mosley, Steven D. Porter, Gregory E. Reinhardt, Kevin Zacchera
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Publication number: 20180298823Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.Type: ApplicationFiled: June 19, 2018Publication date: October 18, 2018Inventors: Kevin Zacchera, Matthew Andrew Hough, Jonathan Lemoine, Christopher Treat, Alberto A. Mateo
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Publication number: 20180292089Abstract: A combustor panel of a combustor may include a combustion facing surface and a cooling surface opposite the combustion facing surface. An attachment feature may extend from the cooling surface. The attachment feature may define a first channel extending through the attachment feature to the combustion facing surface. The combustor channel may be formed by additive manufacturing.Type: ApplicationFiled: April 5, 2017Publication date: October 11, 2018Applicant: United Technologies CorporationInventors: Steven D. Porter, Jonathan Lemoine, Kevin Zacchera