Patents by Inventor Carl Brian Klinetob
Carl Brian Klinetob 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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Publication number: 20150252679Abstract: A static guide vane for use in a fan section of a gas turbine engine includes an outer platform and an inner platform. The inner and outer platforms are connected by an airfoil. The airfoil have channels extending into a main body of the airfoil to reduce the weight of the vane. A cover closes off the channels with the cover providing a portion of the airfoil.Type: ApplicationFiled: March 4, 2013Publication date: September 10, 2015Inventors: Andrew Pope, David J. Yudichak, John P. Lucashu, Gregory E. Reinhardt, John C. Ditomasso, Steven L. Conner, Carl Brian Klinetob, Jason Leroux
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Publication number: 20150226067Abstract: An airfoil array includes a plurality of airfoils that differ in geometry over a plurality of geometry classes. An airfoil can include an airfoil body that has a first distinct piece and a second distinct piece that seats together with the first distinct piece. The first distinct piece and the second distinct piece include a mistake-proof feature configured such that the second distinct piece fully seats with the first distinct piece.Type: ApplicationFiled: February 22, 2013Publication date: August 13, 2015Applicant: United Technologies CorporationInventors: Thomas B. Hyatt, Carl Brian Klinetob
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Publication number: 20150218957Abstract: A seal for use with a static guide vane of a gas turbine engine has a strap member extending to a generally cylindrical bulb. The bulb forms a diameter, and is spaced a distance defined between an end of the strap remote from the bulb, to a point on the bulb furthest from the end. A ratio of the diameter to the distance is between 0.2 and 0.5. A static guide vane and a gas turbine engine are also disclosed.Type: ApplicationFiled: March 1, 2013Publication date: August 6, 2015Inventors: Carl Brian Klinetob, Nicholas D. Stilin
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Publication number: 20140086737Abstract: A disclosed structural guide vane for a gas turbine engine includes a strut defining a plurality of channels and a cover attached over the plurality of channels. The strut includes a first side defining a first surface of an airfoil and a second side including a plurality of channels. At least one of the plurality of channels defines a wall thickness of a portion of the first side that varies in a chord wise direction.Type: ApplicationFiled: December 12, 2012Publication date: March 27, 2014Applicant: United Technologies CorporationInventors: Thomas B. Hyatt, Carl Brian Klinetob, Jason Leroux
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Patent number: 8573947Abstract: A composite fan blade having an airfoil with a leading edge and a trailing edge and a dovetail root includes a first pressure face and second pressure face, a lower horizontal face connecting the pressure faces at the bottom of the dovetail and a first and a second dovetail runout fillet connecting the pressure faces to the airfoil. The pressure faces are each angled outward at about 65 degrees to about 75 degrees from horizontal.Type: GrantFiled: March 10, 2010Date of Patent: November 5, 2013Assignee: United Technologies CorporationInventors: Carl Brian Klinetob, Brian P. Huth, Gregory E. Reinhardt
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Patent number: 8419374Abstract: The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness.Type: GrantFiled: August 14, 2009Date of Patent: April 16, 2013Assignee: Hamilton Sundstrand CorporationInventors: Brian P. Huth, Phillip Alexander, Carl Brian Klinetob, Michael Parkin, Rajiv A. Naik
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Publication number: 20130064676Abstract: A method of forming an airfoil includes forming a metal portion of the airfoil including a tip, a leading edge, a trailing edge, a pressure side and a suction side; forming a plurality of grooves into one side of the airfoil; and filling the plurality of grooves with composite material.Type: ApplicationFiled: September 13, 2011Publication date: March 14, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: George Alan Salisbury, Phillip Alexander, Carl Brian Klinetob
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Patent number: 8376712Abstract: A sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes a solid portion to wrap around the airfoil lead edge and over the airfoil tip and means for securing the solid portion to the airfoil.Type: GrantFiled: January 26, 2010Date of Patent: February 19, 2013Assignee: United Technologies CorporationInventors: Carl Brian Klinetob, Phillip Alexander, Allan J. Brockett
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Patent number: 8257030Abstract: Gas turbine engine systems involving fairings with locating data are provided. In this regard, a representative a fairing assembly for a gas turbine engine includes: a first locating component having a leading edge, first and second sides extending from the leading edge, and a recess oriented parallel to the leading edge, the recess having a first datum surface, the first locating component being operative to be positioned between a portion of a strut and a portion of an interior surface of a fairing sheath such that the first datum surface establishes a desired orientation of the fairing sheath relative to the strut.Type: GrantFiled: March 18, 2008Date of Patent: September 4, 2012Assignee: United Technologies CorporationInventors: David R. Lyders, Carl Brian Klinetob, Phillip Alexander
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Publication number: 20120134839Abstract: A composite airfoil includes a core that has a three-dimensional network of fibers. The core defines an airfoil section and a root section. A composite skin covers a portion of the core excluding the root section.Type: ApplicationFiled: November 29, 2010Publication date: May 31, 2012Inventors: Michael Parkin, Phillip Alexander, Carl Brian Klinetob
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Patent number: 8105042Abstract: An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix.Type: GrantFiled: April 6, 2009Date of Patent: January 31, 2012Assignee: United Technologies CorporationInventors: Michael Parkin, Phillip Alexander, Carl Brian Klinetob, Steven Clarkson
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Publication number: 20110182740Abstract: A sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes a solid portion to wrap around the airfoil lead edge and over the airfoil tip and means for securing the solid portion to the airfoil.Type: ApplicationFiled: January 26, 2010Publication date: July 28, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Carl Brian Klinetob, Phillip Alexander, Allan J. Brockett
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Publication number: 20110129348Abstract: A method of forming a composite airfoil having a suction side and pressure side includes the steps of designing a mold, designing a woven core, designing a plurality of plies and assembling the designed mold, core and plies to create the composite airfoil. The hollow mold has an inner surface which defines the surface profile of the composite airfoil. The plurality of plies is designed to fit between the inner surface of the mold and an outer surface of the woven core. The plurality of plies is designed after the step of designing the woven core.Type: ApplicationFiled: November 30, 2009Publication date: June 2, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Michael Parkin, Phillip Alexander, Brian P. Huth, Carl Brian Klinetob
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Publication number: 20110038732Abstract: The disclosed composite airfoil includes a three-dimensional composite core extending longitudinally and having a chord-wise direction. The core has a core in-plane thickness extending between opposing sides in a through-plane direction generally perpendicular to the chord-wise and longitudinal directions. A composite skin covers the opposing sides and has an exterior surface providing an airfoil contour. The skin includes a total skin in-plane thickness corresponding to a sum of thicknesses through the skin in the through-plane direction from each of the opposing sides to their adjoining exterior surface. A sum of the core in-plane and total skin in-plane thicknesses at a central portion of the composite airfoil is a total in-plane thickness. The total skin in-plane thickness at the central portion is less than 50% of the total in-plane thickness.Type: ApplicationFiled: August 14, 2009Publication date: February 17, 2011Inventors: Brian P. Huth, Phillip Alexander, Carl Brian Klinetob, Michael Parkin, Rajiv A. Naik
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Publication number: 20110033302Abstract: A fan blade includes an airfoil and a dovetail at a radially inner end of the airfoil. The dovetail extends between first and second axial ends, and has outer circumferential faces. The dovetail is formed of relatively rigid composite material. Compliant material is placed on each outer circumferential face of the dovetail. The compliant material is less rigid than the composite material for forming the dovetail. In a second embodiment, the compliant layer may be positioned within the disk slots in a disk, such that the compliant layer will come in contact with circumferentially outer faces of the dovetail.Type: ApplicationFiled: August 5, 2009Publication date: February 10, 2011Inventors: Peter D. Ventura, Carl Brian Klinetob
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Patent number: 7815839Abstract: A mandrel comprising a rigid inner core and an elastomeric outer layer that at least partially surrounds the rigid inner core, wherein the elastomeric outer layer is adapted to expand during a molding process to seal a cavity to prevent incursion of material injected during the molding process.Type: GrantFiled: July 25, 2007Date of Patent: October 19, 2010Assignee: United Technologies CorporationInventors: John H. Vontell, Sr., Carl Brian Klinetob, Christopher John Feeney
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Publication number: 20100254821Abstract: An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix.Type: ApplicationFiled: April 6, 2009Publication date: October 7, 2010Inventors: Michael Parkin, Phillip Alexander, Carl Brian Klinetob, Steven Clarkson
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Publication number: 20090238686Abstract: Gas turbine engine systems involving fairings with locating data are provided. In this regard, a representative a fairing assembly for a gas turbine engine includes: a first locating component having a leading edge, first and second sides extending from the leading edge, and a recess oriented parallel to the leading edge, the recess having a first datum surface, the first locating component being operative to be positioned between a portion of a strut and a portion of an interior surface of a fairing sheath such that the first datum surface establishes a desired orientation of the fairing sheath relative to the strut.Type: ApplicationFiled: March 18, 2008Publication date: September 24, 2009Applicant: UNITED TECHNOLOGIES CORP.Inventors: David R. Lyders, Carl Brian Klinetob, Phillip Alexander
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Patent number: 7549839Abstract: An inlet guide vane provides improved, smooth airflow and avoids separation of flow even at high incidence angles. The inlet guide vane includes a strut having opposite side surfaces that are continuously curved to provide a controlled velocity distribution at the trailing edge of the strut. The inlet guide vane further includes a flap having a leading edge aligned behind the trailing edge of the strut. Generally, the strut and the flap are designed together so that low momentum air in the gap between the strut and the flap will be energized and entrained in the boundary layer of the flap. The airflow from the gap will remain attached to the flap to improve the flow from the flap.Type: GrantFiled: October 25, 2005Date of Patent: June 23, 2009Assignee: United Technologies CorporationInventors: Christian A. Carroll, James Allen Eley, Carl Brian Klinetob
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Publication number: 20090026659Abstract: A mandrel comprising a rigid inner core and an elastomeric outer layer that at least partially surrounds the rigid inner core, wherein the elastomeric outer layer is adapted to expand during a molding process to seal a cavity to prevent incursion of material injected during the molding process.Type: ApplicationFiled: July 25, 2007Publication date: January 29, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: John H. Vontell, SR., Carl Brian Klinetob, Christopher John Feeney