Patents by Inventor Gregory M. Dolansky
Gregory M. Dolansky 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: 10294801Abstract: A rotor blade includes a main body that extends radially outward from a first end to a second end, and includes a platform at the second end that extends circumferentially between opposing first and second sidewalls. The platform includes a first lateral wall that is situated between leading and trailing edges of the platform. The first lateral wall extends circumferentially between the first and second sidewalls and radially outward from the platform. The first lateral wall includes an extension that extends the first lateral wall circumferentially outward from the first sidewall. Respective portions of the first and second sidewalls adjacent to the first lateral wall reside in respective first and second planes, and the extension includes an outer face situated outside of the first and second planes. A majority of the first lateral wall includes a first material, and the outer face includes a second material having a different resistance to wear than the first material.Type: GrantFiled: July 25, 2017Date of Patent: May 21, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: JinQuan Xu, Glenn Levasseur, Gregory M. Dolansky
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Publication number: 20190032498Abstract: A rotor blade includes a main body that extends radially outward from a first end to a second end, and includes a platform at the second end that extends circumferentially between opposing first and second sidewalls. The platform includes a first lateral wall that is situated between leading and trailing edges of the platform. The first lateral wall extends circumferentially between the first and second sidewalls and radially outward from the platform. The first lateral wall includes an extension that extends the first lateral wall circumferentially outward from the first sidewall. Respective portions of the first and second sidewalls adjacent to the first lateral wall reside in respective first and second planes, and the extension includes an outer face situated outside of the first and second planes. A majority of the first lateral wall includes a first material, and the outer face includes a second material having a different resistance to wear than the first material.Type: ApplicationFiled: July 25, 2017Publication date: January 31, 2019Inventors: JinQuan Xu, Glenn Levasseur, Gregory M. Dolansky
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Patent number: 9719363Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.Type: GrantFiled: June 4, 2015Date of Patent: August 1, 2017Assignee: United Technologies CorporationInventors: David R Pack, Julian Partyka, James D. Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
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Patent number: 9404369Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.Type: GrantFiled: April 24, 2012Date of Patent: August 2, 2016Assignee: United Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Benjamin T. Fisk, Steven Taffet, Gregory M. Dolansky, Anita L. Tracy
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Patent number: 9393620Abstract: A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.Type: GrantFiled: December 14, 2012Date of Patent: July 19, 2016Assignee: United Technologies CorporationInventors: Daniel A. Bales, Agnes Klucha, Gregory M. Dolansky
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Patent number: 9249668Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.Type: GrantFiled: April 24, 2012Date of Patent: February 2, 2016Assignee: United Technologies CorporationInventors: Benjamin T. Fisk, Tracy A. Propheter-Hinckley, Gregory M. Dolansky, David P. Houston, Anita L. Tracy
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Publication number: 20150354389Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.Type: ApplicationFiled: June 4, 2015Publication date: December 10, 2015Inventors: David R Pack, Julian Partyka, James D Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
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Patent number: 9181806Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.Type: GrantFiled: April 24, 2012Date of Patent: November 10, 2015Assignee: United Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Gregory M. Dolansky, Benjamin T. Fisk, Robert J. Treen
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Patent number: 9121286Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.Type: GrantFiled: April 24, 2012Date of Patent: September 1, 2015Assignee: United Technologies CorporationInventors: Gregory M. Dolansky, Benjamin T. Fisk, Tracy A. Propheter-Hinckley, Anita L. Tracy
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Patent number: 8915718Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.Type: GrantFiled: April 24, 2012Date of Patent: December 23, 2014Assignee: United Technologies CorporationInventors: Gregory M. Dolansky, Tracy A. Propheter-Hinckley, Benjamin T. Fisk
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Publication number: 20140169981Abstract: A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.Type: ApplicationFiled: December 14, 2012Publication date: June 19, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel A. Bales, Agnes Klucha, Gregory M. Dolansky
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Publication number: 20130280059Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.Type: ApplicationFiled: April 24, 2012Publication date: October 24, 2013Inventors: Gregory M. Dolansky, Benjamin T. Fisk, Tracy A. Propheter-Hlnckley, Anita L. Tracy
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Publication number: 20130280082Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.Type: ApplicationFiled: April 24, 2012Publication date: October 24, 2013Inventors: Tracy A. Propheter-Hinckley, Gregory M. Dolansky, Benjamin T. Fisk, Robert J. Treen
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Publication number: 20130276455Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.Type: ApplicationFiled: April 24, 2012Publication date: October 24, 2013Inventors: Benjamin T. Fisk, Tracy A. Propheter-Hinckley, Gregory M. Dolansky, David P. Houston, Anita L. Tracy
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Publication number: 20130280045Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.Type: ApplicationFiled: April 24, 2012Publication date: October 24, 2013Inventors: Gregory M. Dolansky, Tracy A. Propheter-Hinckley, Benjamin T. Fisk
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Publication number: 20130276460Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.Type: ApplicationFiled: April 24, 2012Publication date: October 24, 2013Inventors: Tracy A. Propheter-Hinckley, Benjamin T. Fisk, Steven Taffet, Gregory M. Dolansky, Anita L. Tracy
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Publication number: 20020194733Abstract: The present invention relates to a method for repairing a turbine blade having a crack in a trailing edge portion of the blade. The method comprises the steps of cutting back a first surface of the turbine blade adjacent the blade trailing edge portion where the crack is located, and cutting back a second surface of the turbine blade adjacent the blade trailing edge portion where the crack is located. Each cut back step comprises cutting back the respective surface by a depth greater than the length of the crack and less than the trailing edge radius to remove the crack and form a cut back trailing edge portion. A compound radius is used to prevent a blunt transition into the trailing edge that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade to increase service life.Type: ApplicationFiled: June 22, 2001Publication date: December 26, 2002Inventors: Raymond C. Surace, Brian D. Merry, Gregory M. Dolansky, Gregory E. Reinhardt
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Patent number: 6490791Abstract: A method for repairing a turbine blade having a crack in a trailing edge portion of the blade includes the steps of cutting back a first surface of the turbine blade adjacent the blade trailing edge portion where the crack is located, and cutting back a second surface of the turbine blade adjacent the blade trailing edge portion where the crack is located. Each cut back step comprises cutting back the respective surface by a depth greater than the length of the crack and less than the trailing edge radius to remove the crack and form a cut back trailing edge portion. A compound radius is used to prevent a blunt transition into the trailing edge that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade to increase service life. Prior to applying the coating, the tip portion of the turbine blade is modified to account for the change in the thermal characteristics of the turbine blade.Type: GrantFiled: June 22, 2001Date of Patent: December 10, 2002Assignee: United Technologies CorporationInventors: Raymond C. Surace, Brian D. Merry, Gregory M. Dolansky, Gregory E. Reinhardt