Patents by Inventor Rajiv A. Naik
Rajiv A. Naik 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: 11085456Abstract: A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction.Type: GrantFiled: August 22, 2016Date of Patent: August 10, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Larry Foster, Rajiv A. Naik, John D. Riehl
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Patent number: 10717109Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.Type: GrantFiled: April 27, 2018Date of Patent: July 21, 2020Assignee: Raytheon Technologies CorporationInventors: Rajiv A. Naik, John D. Riehl, Larry Foster
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Publication number: 20180243788Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.Type: ApplicationFiled: April 27, 2018Publication date: August 30, 2018Applicant: United Technologies CorporationInventors: Rajiv A. Naik, John D. Riehl, Larry Foster
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Patent number: 10048180Abstract: A coating bond test method includes, attaching with an adhesive a pull-off bar to a coating on a planar surface of a substrate for which a normal bond strength between the coating and the substrate is sought, reducing a first area defined by an interface between the substrate and the coating to a value less than a second area defined by an interface between the adhesive and the coating, urging the pull-off bar away from the substrate in a direction normal to the planar surface until failure occurs, and recording a load at which failure occurred.Type: GrantFiled: October 16, 2015Date of Patent: August 14, 2018Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: JinKyu Choi, Rajiv A. Naik
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Patent number: 9987659Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.Type: GrantFiled: October 19, 2015Date of Patent: June 5, 2018Assignee: United Technologies CorporationInventors: Rajiv A Naik, John D Riehl, Larry Foster
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Publication number: 20180051705Abstract: A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction.Type: ApplicationFiled: August 22, 2016Publication date: February 22, 2018Inventors: Larry Foster, Rajiv A. Naik, John D. Riehl
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Publication number: 20170234784Abstract: A coating bond test method includes, attaching with an adhesive a pull-off bar to a coating on a planar surface of a substrate for which a normal bond strength between the coating and the substrate is sought, reducing a first area defined by an interface between the substrate and the coating to a value less than a second area defined by an interface between the adhesive and the coating, urging the pull-off bar away from the substrate in a direction normal to the planar surface until failure occurs, and recording a load at which failure occurred.Type: ApplicationFiled: October 16, 2015Publication date: August 17, 2017Inventors: JinKyu Choi, Rajiv A. Naik
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Publication number: 20170106407Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.Type: ApplicationFiled: October 19, 2015Publication date: April 20, 2017Inventors: Rajiv A. Naik, John D. Riehl, Larry Foster
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Publication number: 20150275689Abstract: A fan case for a gas turbine engine includes a composite fan containment case that includes an outer surface. The composite fan containment case includes multiple composite layers that define a generally cylindrical case. An attachment flange extends radially outward from the cylindrical case. The attachment flange comprises a portion of the composite layers. A metallic backing ring is secured to the attachment flange by rivets.Type: ApplicationFiled: January 23, 2014Publication date: October 1, 2015Applicant: United Technologies CorporationInventors: Darin S. Lussier, Thomas J. Robertson, JR., Mark W. Costa, Sreenivasa R. Voleti, Rajiv A. Naik
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Patent number: 8827629Abstract: A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.Type: GrantFiled: February 10, 2011Date of Patent: September 9, 2014Assignee: United Technologies CorporationInventors: Sreenivasa R. Voleti, Darin S. Lussier, Rajiv A. Naik
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Patent number: 8696319Abstract: A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.Type: GrantFiled: May 2, 2013Date of Patent: April 15, 2014Assignee: United Technologies CorporationInventor: Rajiv A. Naik
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Patent number: 8672609Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.Type: GrantFiled: February 16, 2012Date of Patent: March 18, 2014Assignee: United Technologies CorporationInventors: Darin S. Lussier, Thomas J. Robertson, Jr., Mark W. Costa, Sreenivasa R. Voleti, Rajiv A. Naik
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Patent number: 8662855Abstract: A composite blade includes a preform and a binder. The preform is a preform of yarns woven in three-dimensions and has a tip region, a root region and an intermediate region. The intermediate region is positioned between the tip region and the root region. The yarns comprise warp yarns and weft yarns. The warp yarns form a longitudinal axis. The weft yarns are positioned at a 90 degree angle to the warp yarns. The weft yarns increase in yarn size as determined by filament count along the longitudinal axis to change the thickness of the preform. The binder maintains the relative positions of the preform yarns.Type: GrantFiled: August 31, 2010Date of Patent: March 4, 2014Assignee: United Technologies CorporationInventors: Rajiv A. Naik, Steven R. Clarke
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Publication number: 20130243603Abstract: A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.Type: ApplicationFiled: May 2, 2013Publication date: September 19, 2013Applicant: United Technologies CorporationInventor: Rajiv A. Naik
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Patent number: 8499450Abstract: A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.Type: GrantFiled: January 26, 2010Date of Patent: August 6, 2013Assignee: United Technologies CorporationInventor: Rajiv A. Naik
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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: 20120207583Abstract: A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.Type: ApplicationFiled: February 10, 2011Publication date: August 16, 2012Inventors: Sreenivasa R. Voleti, Darin S. Lussier, Rajiv A. Naik
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Publication number: 20120148392Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.Type: ApplicationFiled: February 16, 2012Publication date: June 14, 2012Inventors: Darin S. LUSSIER, Thomas J. ROBERTSON, JR., Mark W. COSTA, Sreenivasa R. VOLETI, Rajiv A. NAIK
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Publication number: 20120051935Abstract: A composite blade includes a preform and a binder. The preform is a preform of yarns woven in three-dimensions and has a tip region, a root region and an intermediate region. The intermediate region is positioned between the tip region and the root region. The yarns comprise warp yarns and weft yarns. The warp yarns form a longitudinal axis. The weft yarns are positioned at a 90 degree angle to the warp yarns. The weft yarns increase in yarn size as determined by filament count along the longitudinal axis to change the thickness of the preform. The binder maintains the relative positions of the preform yarns.Type: ApplicationFiled: August 31, 2010Publication date: March 1, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Rajiv A. Naik, Steven R. Clarke
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Publication number: 20110182743Abstract: A composite blade has a root and a tip in a spanwise direction and a leading edge and a trailing edge in a chordwise direction. The composite blade includes a three-dimensional woven preform having weft yarns and warp yarns. The weft yarns extend in the spanwise direction of the composite blade. The warp yarns interweave the weft yarns and extend in the chordwise direction of the blade.Type: ApplicationFiled: January 26, 2010Publication date: July 28, 2011Applicant: United Technologies CorporationInventor: Rajiv A. Naik