Patents by Inventor Michael Todd Radwanski
Michael Todd Radwanski 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: 11761342Abstract: A sealing assembly for a gas turbine engine. The sealing assembly includes first and second gas turbine walls defining a channel therebetween. Additionally, the second gas turbine wall further defines a passage extending therethrough. Furthermore, the sealing assembly includes a leaf seal partially positioned within the channel and a seal holder coupled to the second gas turbine wall. Moreover, the sealing assembly includes a spring compressed between the seal holder and the leaf seal such that the leaf seal is in sealing engagement with the first gas turbine wall. In addition, the sealing assembly includes a pin extending through the passage defined by the second gas turbine wall to couple the seal holder and the leaf seal such that the pin is thermally unconstrained by the second wall during operation of the gas turbine engine.Type: GrantFiled: October 26, 2020Date of Patent: September 19, 2023Assignee: General Electric CompanyInventors: Michael Todd Radwanski, Darrell Glenn Senile
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Publication number: 20220127967Abstract: A sealing assembly for a gas turbine engine. The sealing assembly includes first and second gas turbine walls defining a channel therebetween. Additionally, the second gas turbine wall further defines a passage extending therethrough. Furthermore, the sealing assembly includes a leaf seal partially positioned within the channel and a seal holder coupled to the second gas turbine wall. Moreover, the sealing assembly includes a spring compressed between the seal holder and the leaf seal such that the leaf seal is in sealing engagement with the first gas turbine wall. In addition, the sealing assembly includes a pin extending through the passage defined by the second gas turbine wall to couple the seal holder and the leaf seal such that the pin is thermally unconstrained by the second wall during operation of the gas turbine engine.Type: ApplicationFiled: October 26, 2020Publication date: April 28, 2022Inventors: Michael Todd Radwanski, Darrell Glenn Senile
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Patent number: 11268697Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: GrantFiled: August 12, 2019Date of Patent: March 8, 2022Assignee: General Electric CompanyInventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Patent number: 11092023Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: GrantFiled: January 31, 2018Date of Patent: August 17, 2021Assignee: General Electric CompanyInventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps
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Publication number: 20200088051Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: ApplicationFiled: January 31, 2018Publication date: March 19, 2020Inventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps
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Publication number: 20200003418Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: ApplicationFiled: August 12, 2019Publication date: January 2, 2020Inventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Patent number: 10378769Abstract: Combustor assemblies having heat shields heat shield attachment features are provided. For example, a combustor assembly includes a dome plate defining first and second apertures, and a heat shield defining first and second openings. The heat shield includes a first cup extending about the first opening and a second cup extending about the second opening. The combustor assembly further includes a collar having a first frame at least partially surrounding the first cup and a second frame at least partially surrounding the second cup. The collar includes a first fastening feature and the dome plate includes a second fastening feature. The first fastening feature mates with the second fastening feature to couple the heat shield to the dome plate. The combustor assembly also may include an attachment piece configured to couple the heat shield to the dome plate. Methods for forming ceramic matrix composite (CMC) heat shields also are provided.Type: GrantFiled: September 30, 2016Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Michael Todd Radwanski, Michael Alan Stieg, Donald Michael Corsmeier
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Patent number: 10378772Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: GrantFiled: January 19, 2017Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Patent number: 10371383Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.Type: GrantFiled: January 27, 2017Date of Patent: August 6, 2019Assignee: General Electric CompanyInventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Andrew Scott Bilse, Michael Todd Radwanski, Ernesto Andres Vallejo Ruiz, Aaron Michael Dziech, Mark Eugene Noe
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Patent number: 10132197Abstract: Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.Type: GrantFiled: April 20, 2015Date of Patent: November 20, 2018Assignee: General Electric CompanyInventors: Bryce Loring Heitman, Michael Todd Radwanski, Darrell Glenn Senile
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Publication number: 20180216824Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.Type: ApplicationFiled: January 27, 2017Publication date: August 2, 2018Inventors: Brandon ALlanson Reynolds, Jonathan David Baldiga, Andrew Scott Bilse, Michael Todd Radwanski, Ernesto Andres Vallejo Ruiz, Aaron Michael Dziech, Mark Eugene Noe
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Publication number: 20180202659Abstract: Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.Type: ApplicationFiled: January 19, 2017Publication date: July 19, 2018Inventors: Michael Alan Stieg, Valeria Proano Cadena, Aaron Michael Dziech, Michael Todd Radwanski, Donald Michael Corsmeier
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Patent number: 9964309Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.Type: GrantFiled: December 22, 2014Date of Patent: May 8, 2018Assignee: General Electric CompanyInventors: Donald Michael Corsmeier, Mark Eugene Noe, Michael Todd Radwanski, Oliver Roghe, Jessica Licardi Subit, Ming Xie
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Publication number: 20180094811Abstract: Combustor assemblies having heat shields heat shield attachment features are provided. For example, a combustor assembly includes a dome plate defining first and second apertures, and a heat shield defining first and second openings. The heat shield includes a first cup extending about the first opening and a second cup extending about the second opening. The combustor assembly further includes a collar having a first frame at least partially surrounding the first cup and a second frame at least partially surrounding the second cup. The collar includes a first fastening feature and the dome plate includes a second fastening feature. The first fastening feature mates with the second fastening feature to couple the heat shield to the dome plate. The combustor assembly also may include an attachment piece configured to couple the heat shield to the dome plate. Methods for forming ceramic matrix composite (CMC) heat shields also are provided.Type: ApplicationFiled: September 30, 2016Publication date: April 5, 2018Inventors: Michael Todd Radwanski, Michael Alan Stieg, Donald Michael Corsmeier
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Patent number: 9915159Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: GrantFiled: December 18, 2014Date of Patent: March 13, 2018Assignee: General Electric CompanyInventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Greg Scott Phelps
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Patent number: 9546557Abstract: A nozzle, a nozzle hanger, and a ceramic to metal attachment system are provided. The ceramic to metal attachment system includes the nozzle, a ceramic matrix composite, and the nozzle hanger, a metal. The attachment system also includes a clamping member adjacent a second surface of the nozzle and a mounting member of the nozzle. The attachment system includes a plurality of attachment members securing the nozzle, the clamping member, and the nozzle hanger together. A sealing member of the nozzle hanger seals off an airfoil of the nozzle from adjacent airflow.Type: GrantFiled: March 14, 2013Date of Patent: January 17, 2017Assignee: General Electric CompanyInventors: James Hamilton Grooms, III, Darrell Glenn Senile, Charles Thomas McMillan, Michael Todd Radwanski
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Publication number: 20160305286Abstract: Shrouds and shroud assemblies for gas turbine engines are provided. A shroud includes a shroud body. The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange extending from the shroud body, and a bore hole defined in the flange. The bore hole extends generally circumferentially through the flange between a first opening and a second opening.Type: ApplicationFiled: April 20, 2015Publication date: October 20, 2016Inventors: Bryce Loring Heitman, Michael Todd Radwanski, Darrell Glenn Senile
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Publication number: 20160177761Abstract: A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.Type: ApplicationFiled: December 18, 2014Publication date: June 23, 2016Inventors: Benjamin Scott Huizenga, Christopher Charles Glynn, Darrell Glenn Senile, Robert Alan Frederick, Michael Todd Radwanski, Michael Ray Tuertscher, Gregg Scott Phelps
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Publication number: 20150107109Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.Type: ApplicationFiled: December 22, 2014Publication date: April 23, 2015Inventors: Donald Michael Corsmeier, Mark Eugene Noe, Michael Todd Radwanski, Oliver Roghe, Jessica Licardi Subit, Ming Xie
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Patent number: 8943835Abstract: A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.Type: GrantFiled: May 10, 2010Date of Patent: February 3, 2015Assignee: General Electric CompanyInventors: Donald Michael Corsmeier, Mark Eugene Noe, Michael Todd Radwanski, Oliver Roghe, Jessica Licardi Subit, Ming Xie