Patents by Inventor Robert Alan Frederick
Robert Alan Frederick 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: 11230935Abstract: One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.Type: GrantFiled: September 18, 2015Date of Patent: January 25, 2022Assignee: General Electric CompanyInventors: Benjamin Scott Huizenga, Darrell Glenn Senile, Robert Alan Frederick, Paul Joseph Kreitzer
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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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Patent number: 10301954Abstract: A ceramic airfoil is provided. The ceramic airfoil may include a leading edge, a trailing edge, and a pair of sidewalls. The pair of sidewalls may include a suction sidewall and a pressure sidewall spaced apart in a widthwise direction and extending in the chordwise direction between the leading edge and the trailing edge. The pair of sidewalls may also define cooling cavity and a plurality of internal cooling passages downstream of the cooling cavity to receive a pressurized cooling airflow. The internal cooling passages may be defined across a diffusion section with a set diffusion length, and include one or more predefined ratios or angles.Type: GrantFiled: January 8, 2016Date of Patent: May 28, 2019Assignee: General Electric CompanyInventors: Jason Randolph Allen, Robert Alan Frederick, Robert David Briggs, Michael Ray Tuertscher
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Patent number: 10161257Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectively. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.Type: GrantFiled: October 20, 2015Date of Patent: December 25, 2018Assignee: General Electric CompanyInventors: Benjamin Scott Huizenga, Kevin Robert Feldmann, Robert Alan Frederick, Robert Charles Groves, II, Kirk Douglas Gallier, Timothy Francis Andrews, Darrell Senile
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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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Publication number: 20170198595Abstract: A ceramic airfoil is provided. The ceramic airfoil may include a leading edge, a trailing edge, and a pair of sidewalls. The pair of sidewalls may include a suction sidewall and a pressure sidewall spaced apart in a widthwise direction and extending in the chordwise direction between the leading edge and the trailing edge. The pair of sidewalls may also define cooling cavity and a plurality of internal cooling passages downstream of the cooling cavity to receive a pressurized cooling airflow. The internal cooling passages may be defined across a diffusion section with a set diffusion length, and include one or more predefined ratios or angles.Type: ApplicationFiled: January 8, 2016Publication date: July 13, 2017Inventors: Jason Randolph Allen, Robert Alan Frederick, Robert David Briggs, Michael Ray Tuertscher
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Publication number: 20170107837Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.Type: ApplicationFiled: October 20, 2015Publication date: April 20, 2017Inventors: Benjamin Scott Huizenga, Kevin Robert Feldmann, Robert Alan Frederick, Robert Charles Groves, II, Kirk Douglas Gallier, Timothy Francis Andrews, Darrell Senile
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Publication number: 20170081966Abstract: One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.Type: ApplicationFiled: September 18, 2015Publication date: March 23, 2017Inventors: Benjamin Scott HUIZENGA, Darrell Glenn SENILE, Robert Alan FREDERICK, Paul Joseph KREITZER
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Patent number: 9581085Abstract: Embodiments of hot streak alignment for gas turbine durability include structures and methods to align hot streaks with the leading edges of aligned first stage nozzle vanes in order to improve mixing of the hot streaks with cooling air at a stator nozzle of a first stage turbine and reduce usage of cooling air at first stage non-aligned stator nozzle vanes disposed adjacent to the aligned stator vanes.Type: GrantFiled: March 15, 2013Date of Patent: February 28, 2017Assignee: General Electric CompanyInventors: Robert Joseph Bartz, Joseph Steven Bubnick, Scott Matthew Bush, Kevin Robert Feldmann, Robert Alan Frederick, Craig William Higgins
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Patent number: 9506351Abstract: A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures.Type: GrantFiled: March 28, 2013Date of Patent: November 29, 2016Assignee: General Electric CompanyInventors: Joseph Steven Bubnick, Robert Joseph Bartz, Daniel Edward Demers, Robert Alan Frederick, Todd Stephen Heffron, Sean Michael Molleson
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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: 20140003937Abstract: A component and method of cooling a component are provided. The component includes a leading edge, a trailing edge, at least one cavity between the leading edge and the trailing edge, at least one diffusion member adjacent to the cavity. The diffusion member includes an inlet adjacent to the cavity, a metering zone adjacent to the inlet, a diffusion zone adjacent to the metering zone, and an outlet adjacent the diffusion zone and adjacent the trailing edge. The diffusion member provides up to about 70% reduction in flow and uniform cooling of the trailing edge of the component.Type: ApplicationFiled: March 14, 2013Publication date: January 2, 2014Applicant: General Electric CompanyInventors: James Hamilton GROOMS, Darrell Glenn SENILE, Robert Alan FREDERICK
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Publication number: 20140004293Abstract: A ceramic matrix composite (CMC) component and a method of attaching a static seal to a ceramic matrix composite component are provided. The CMC component includes a first end and a second end. A CMC metal interface member is attached to the second end. The CMC metal interface member is operable to join to a static seal in a gas turbine.Type: ApplicationFiled: March 14, 2013Publication date: January 2, 2014Applicant: General Electric CompanyInventors: James Hamilton GROOMS, II, Darrell Glenn Senile, Robert Alan Frederick, Charles Thomas McMillan
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Patent number: 7007488Abstract: A gas turbine engine includes a compressor powered by a turbine. The turbine includes a nozzle having vanes extending between outer and inner bands. Each vane includes an internal cooling plenum and a bypass tube extending through the bands. First and second manifolds surround the outer band and are disposed in flow communication with the plenums and bypass tubes, respectively. A bleed circuit joins the compressor to the manifolds for providing pressurized air thereto. A control valve modulates airflow to the first manifold and in turn through the cooling plenums of the vanes.Type: GrantFiled: July 6, 2004Date of Patent: March 7, 2006Assignee: General Electric CompanyInventors: Robert Joseph Orlando, Thomas Ory Moniz, John Christopher Brauer, Ian Francis Prentice, Erich Alois Krammer, James Patrick Dolan, Robert Alan Frederick
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Patent number: 7008185Abstract: A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.Type: GrantFiled: February 27, 2003Date of Patent: March 7, 2006Assignee: General Electric CompanyInventors: Jonathan Jordan Peterman, Andrew Charles Powis, Ronald Eugene McRae, Jr., Jonathan Philip Clarke, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Patent number: 6969233Abstract: A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.Type: GrantFiled: February 27, 2003Date of Patent: November 29, 2005Assignee: General Electric CompanyInventors: Andrew Charles Powis, Ronald Eugene McRae, Jr., Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Patent number: 6932568Abstract: A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.Type: GrantFiled: February 27, 2003Date of Patent: August 23, 2005Assignee: General Electric CompanyInventors: Andrew Charles Powis, Ronald Eugene McRae, Jr., Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Publication number: 20040170499Abstract: A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.Type: ApplicationFiled: February 27, 2003Publication date: September 2, 2004Inventors: Andrew Charles Powis, Ronald Eugene McRae, Jonathan Philip Clarke, Jonathan Jordan Peterman, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith
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Publication number: 20040170498Abstract: A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.Type: ApplicationFiled: February 27, 2003Publication date: September 2, 2004Inventors: Jonathan Jordan Peterman, Andrew Charles Powis, Ronald Eugene McRae, Jonathan Philip Clarke, Robert Alan Frederick, Edward Eugene Gibler, Brian David Keith