Patents by Inventor Michael Anthony Ruthemeyer
Michael Anthony Ruthemeyer 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: 11746703Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: GrantFiled: July 7, 2021Date of Patent: September 5, 2023Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Publication number: 20210340912Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: ApplicationFiled: July 7, 2021Publication date: November 4, 2021Inventors: Michael Anthony RUTHEMEYER, Darrell Glenn SENILE, Bernard James RENGGLI, Randy Lee LEWIS
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Patent number: 11078845Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: GrantFiled: September 6, 2018Date of Patent: August 3, 2021Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Publication number: 20200025087Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: ApplicationFiled: September 6, 2018Publication date: January 23, 2020Inventors: Michael Anthony RUTHEMEYER, Darrell Glenn SENILE, Bernard James RENGGLI, Randy Lee LEWIS
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Patent number: 10221712Abstract: The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap therebetween, and the first and the third shroud segments define a gap therebetween. A first seal portion is positioned at least partially on the first and the third shroud segments and at least partially covers the gap defined by the first and the third shroud segments. A second seal portion is positioned at least partially on the first and the second shroud segments and at least partially covers the gap defined by the first and the second shroud segments. A third seal portion extends between and couples the first and the second seal portions.Type: GrantFiled: May 16, 2016Date of Patent: March 5, 2019Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, David Alan Frey
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Patent number: 10161266Abstract: A nozzle for a gas turbine engine, including an airfoil having an exterior surface, flange and radially compressive contact face. Also included is an airfoil support frame having a mating face positioned in engagement with the contact face. A non-orthogonal engagement angle is provided in order to transmit a compressive force to the airfoil.Type: GrantFiled: September 23, 2015Date of Patent: December 25, 2018Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Richard William Albrecht, Jr., Darrell Glenn Senile
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Patent number: 10132242Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: GrantFiled: April 26, 2013Date of Patent: November 20, 2018Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Publication number: 20170328228Abstract: The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap therebetween, and the first and the third shroud segments define a gap therebetween. A first seal portion is positioned at least partially on the first and the third shroud segments and at least partially covers the gap defined by the first and the third shroud segments. A second seal portion is positioned at least partially on the first and the second shroud segments and at least partially covers the gap defined by the first and the second shroud segments. A third seal portion extends between and couples the first and the second seal portions.Type: ApplicationFiled: May 16, 2016Publication date: November 16, 2017Inventors: Michael Anthony Ruthemeyer, David Alan Frey
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Publication number: 20170328235Abstract: A turbine nozzle assembly includes an outer band and an inner band positioned radially inward from the outer band, wherein a gas flow path is defined between the outer and inner band. The turbine nozzle assembly further includes a stator vane extending radially inward from the outer band to the inner band through the gas flow path. In addition, the outer band of the turbine nozzle assembly defines a cavity and a first conduit extending from an inlet to the cavity. The outer band further defines a second conduit extending from the cavity to an outlet such that the cavity is in fluid communication with the gas flow path through the second conduit.Type: ApplicationFiled: May 16, 2016Publication date: November 16, 2017Inventors: Michael Anthony Ruthemeyer, David Alan Frey
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Publication number: 20170082062Abstract: A nozzle for a gas turbine engine, including an airfoil having an exterior surface, flange and radially compressive contact face. Also included is an airfoil support frame having a mating face positioned in engagement with the contact face. A non-orthogonal engagement angle is provided in order to transmit a compressive force to the airfoil.Type: ApplicationFiled: September 23, 2015Publication date: March 23, 2017Inventors: Michael Anthony Ruthemeyer, Richard William Albrecht, JR., Darrell Glenn Senile
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Publication number: 20150075176Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: ApplicationFiled: April 26, 2013Publication date: March 19, 2015Applicant: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Patent number: 8961114Abstract: One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.Type: GrantFiled: November 22, 2010Date of Patent: February 24, 2015Assignee: General Electric CompanyInventor: Michael Anthony Ruthemeyer
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Publication number: 20120128467Abstract: One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.Type: ApplicationFiled: November 22, 2010Publication date: May 24, 2012Inventor: Michael Anthony Ruthemeyer
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Patent number: 7452183Abstract: A shroud assembly is provided for a gas turbine engine having a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes at least one arcuate shroud segment adapted to surround a row of rotating turbine blades. The shroud segment has an arcuate, axially extending mounting flange. A shroud hanger includes an arcuate, axially-extending hook. A dimension of one of the shroud segments and the shroud hanger are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.Type: GrantFiled: August 6, 2005Date of Patent: November 18, 2008Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Glenn Herbert Nichols, Ching-Pang Lee
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Patent number: 7448846Abstract: A shroud segment is adapted to surround a row of rotating turbine blades in a gas turbine engine. The shroud segment includes: an arcuate, axially extending first mounting flange having a first radius of curvature, and an arcuate, axially extending first overhang having a second radius of curvature. The overhang is disposed parallel to and radially inboard of the first mounting flange so that a first groove is defined between the first mounting flange and the first overhang. The first and second radii of curvature are substantially different from each other. The shroud segment may attached to a supporting structure or shroud hanger to form a shroud assembly.Type: GrantFiled: August 6, 2005Date of Patent: November 11, 2008Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Glenn Herbert Nichols, Ching-Pang Lee
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Patent number: 7442004Abstract: A C-clip for a gas turbine engine includes an arcuate outer arm having a first radius of curvature; an arcuate, inner arm having a second radius of curvature which is substantially greater than the first radius of curvature; and an arcuate extending flange connecting the outer and inner arms. The flange, the outer arm, and the inner arm collectively define a generally C-shaped cross-section. A shroud assembly includes a shroud segment with a mounting flange, and a shroud hanger with an arcuate hook disposed in mating relationship to the mounting flange. An arcuate C-clip having inner and outer arms overlaps the hook and the mounting flange. The shroud segment and the C-clip are subject to thermal expansion at the hot operating condition. A dimension of one of the shroud segment and the C-clip are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.Type: GrantFiled: August 6, 2005Date of Patent: October 28, 2008Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Glenn Herbert Nichols, Ching-Pang Lee
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Patent number: 7438520Abstract: A shroud assembly is provided for a gas turbine engine that has a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes: at least one arcuate shroud segment adapted to surround a row of rotating turbine blades which has an arcuate, axially extending mounting flange; a shroud hanger having an arcuate, axially-extending hook disposed in mating relationship to the mounting flange; and an arcuate C-clip having inner and outer arms overlapping the hook and the mounting flange. The curvatures of the mounting flange and the inner arm of the C-clip are selected so as to define a matched interface therebetween. Their curvatures are substantially greater that the curvature of the hook.Type: GrantFiled: August 6, 2005Date of Patent: October 21, 2008Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Glenn Herbert Nichols, Ching-Pang Lee