Patents by Inventor Darrell Senile
Darrell Senile 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: 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: 9995160Abstract: An airfoil profile-shaped seal is disposable between an inside surface of a hollow airfoil body and a seal support. The seal includes an elongated member defining a generally closed curve having a generally straight portion, a generally curved portion, and having a solid cross-section across and along the length of the elongated member. When the seal is disposed in an airfoil profile-shaped groove of a seal support adjacent to the inner surface of the hollow airfoil body, and a fluid pressure on one side of the seal is greater than a fluid pressure on the other side of the seal, portions of the seal engage the inner surface of the hollow airfoil body and a surface of the groove to form a seal to inhibit leakage of fluid from the one side to the other side.Type: GrantFiled: December 22, 2014Date of Patent: June 12, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Neelesh Nandkumar Sarawate, Kirk D. Gallier, Robert Frederick, Darrell Senile, Benjamin Huizenga
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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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Patent number: 8642170Abstract: A coating system that includes a plurality of portions, each portion comprising one or more layers. The coating system includes an outer portion, which is an infrared radiation (IR) interaction portion, that dissipates incident (IR). Underlying this outer portion is a performance portion. The performance portion comprises at least one layer that includes microspheres. Between the substrate and performance portion is a compliance portion. The compliance portion comprises at least one layer of high temperature material that has a coefficient of thermal expansion (CTE) intermediate the performance layer and the substrate. The compliance portion thus reduces any high temperature thermal mismatch between the substrate and the performance portion.Type: GrantFiled: December 31, 2007Date of Patent: February 4, 2014Assignee: General Electric CompanyInventors: Daniel P. Ivkovich, William Randolph Stowell, Darrell Senile, Thomas W. Rentz, John F. Ackerman
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Publication number: 20090169898Abstract: A coating system that includes a plurality of portions, each portion comprising one or more layers. The coating system includes an outer portion, which is an infrared radiation (IR) interaction portion, that dissipates incident (IR). Underlying this outer portion is a performance portion. The performance portion comprises at least one layer that includes microspheres. Between the substrate and performance portion is a compliance portion. The compliance portion comprises at least one layer of high temperature material that has a coefficient of thermal expansion (CTE) intermediate the performance layer and the substrate. The compliance portion thus reduces any high temperature thermal mismatch between the substrate and the performance portion.Type: ApplicationFiled: December 31, 2007Publication date: July 2, 2009Applicant: General Electric CompanyInventors: Daniel P. Ivkovich, William Randolph Stowell, Darrell Senile, Thomas W. Rentz, John F. Ackerman
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Publication number: 20050235628Abstract: A gas turbine engine exhaust nozzle includes a divergent section located aft of a convergent section and a throat therebetween. An exterior fairing is spaced radially outwardly of the divergent section. An ejector cooling air flowpath leads from an ejector cooling air inlet in an aft portion of the fairing to a cooling air ejector in the nozzle. An annular nozzle plenum may be disposed between the divergent section of the nozzle and the external fairing and be part of the ejector cooling air flowpath between the ejector cooling air inlet and the ejector. A plurality of divergent flaps and divergent seals in the divergent section may employ cooling air passages, such as slots, to serve as the ejector. The fairing may include a plurality of circumferentially adjacent exterior flaps and exterior seals and employ truncated ends of or apertures in the exterior seals as the ejector cooling air inlet.Type: ApplicationFiled: April 21, 2004Publication date: October 27, 2005Inventor: Darrell Senile
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Publication number: 20050091983Abstract: A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a downstream side, forming at least one relief cut in the basesheet that extends at least partially across the basesheet from at least one of the circumferentially-spaced sides, and coupling the basesheet to the backbone assembly.Type: ApplicationFiled: October 29, 2003Publication date: May 5, 2005Inventors: Darrell Senile, Christina Burke, Bernard Renggli, John Amneus
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Patent number: 6745570Abstract: A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates extending a useful life of the exhaust nozzle. The method includes providing a flap basesheet having a width defined between a pair of side edges that are coupled together by a leading edge and a trailing edge, and including at least one stiffener that extends between the basesheet side edges and includes an intermediate portion that has a width that is smaller than that of the basesheet and is at least one of bonded to and formed integrally with the basesheet, and coupling the basesheet to the gas turbine engine with a backbone assembly.Type: GrantFiled: February 1, 2002Date of Patent: June 8, 2004Assignee: General Electric Co.Inventors: Bernard J. Renggli, Darrell Senile
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Patent number: 6739050Abstract: A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.Type: GrantFiled: October 13, 2003Date of Patent: May 25, 2004Assignee: General Electric CompanyInventors: Darrell Senile, Bernard J. Renggli
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Publication number: 20040040308Abstract: A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.Type: ApplicationFiled: October 13, 2003Publication date: March 4, 2004Inventors: Darrell Senile, Bernard J. Renggli
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Patent number: 6658854Abstract: A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.Type: GrantFiled: February 1, 2002Date of Patent: December 9, 2003Assignee: General Electric Co.Inventors: Darrell Senile, Bernard J. Renggli
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Publication number: 20030145599Abstract: A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates extending a useful life of the exhaust nozzle. The method includes providing a flap basesheet having a width defined between a pair of side edges that are coupled together by a leading edge and a trailing edge, and including at least one stiffener that extends between the basesheet side edges and includes an intermediate portion that has a width that is smaller than that of the basesheet and is at least one of bonded to and formed integrally with the basesheet, and coupling the basesheet to the gas turbine engine with a backbone assembly.Type: ApplicationFiled: February 1, 2002Publication date: August 7, 2003Inventors: Bernard J. Renggli, Darrell Senile
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Publication number: 20030145600Abstract: A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method includes attaching an attachment system including at least one strap to a basesheet, and coupling the basesheet to a backbone using the attachment system strap.Type: ApplicationFiled: February 1, 2002Publication date: August 7, 2003Inventors: Darrell Senile, Bernard J. Renggli