Patents by Inventor Thomas J. Robertson, JR.
Thomas J. Robertson, JR. 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: 11248538Abstract: A split case assembly for a gas turbine engine includes an outer diameter case defining a partial case structure for a gas turbine engine and multiple fixed-variable vanes attached to an inner diameter surface of the outer diameter case. Each of the fixed-variable vanes protrudes radially inward from the outer diameter case. Each of the fixed-variable vanes in the plurality of fixed-variable vanes is interfaced with one of a plurality of inner diameter boxes at a radially inward end of the fixed-variable vane, such that the inner diameter boxes define an inner diameter of a flow path and the outer diameter case defines an outer diameter flow path. Each of the fixed-variable vanes are interfaced with the one of the plurality of inner diameter boxes through at least one inner diameter shoe in a plurality of inner diameter shoes.Type: GrantFiled: September 18, 2015Date of Patent: February 15, 2022Assignee: Raytheon Technologies CorporationInventors: Thomas J. Robertson, Jr., Nathan F. Champion, Steven J. Feigleson
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Patent number: 11073027Abstract: An airfoil bonding system may comprise a mold tool configured to support an airfoil assembly during a bonding process. The bonding process may include applying heat and pressure to the airfoil assembly. A surface of the mold tool may complement a preselected airfoil parameter. The mold tool may maintain the airfoil assembly in the preselected airfoil parameter during the application of heat and pressure to the airfoil assembly.Type: GrantFiled: May 17, 2018Date of Patent: July 27, 2021Assignee: Raytheon Technologies CorporationInventors: Thomas J. Robertson, Jr., Carney R. Anderson, Peter T. Schutte
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Patent number: 10731511Abstract: A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.Type: GrantFiled: February 22, 2013Date of Patent: August 4, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Sreenivasa R. Voleti, Mark W. Costa, Steven Clarkson
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Patent number: 10724397Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.Type: GrantFiled: December 8, 2017Date of Patent: July 28, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
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Patent number: 10669936Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.Type: GrantFiled: March 12, 2014Date of Patent: June 2, 2020Assignee: Raytheon Technologies CorporationInventors: Thomas J. Robertson, Jr., Mark W. Costa, David A. Welch
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Patent number: 10487693Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.Type: GrantFiled: February 5, 2018Date of Patent: November 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Mark W. Costa, Steven Clarkson
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Publication number: 20190353040Abstract: An airfoil bonding system may comprise a mold tool configured to support an airfoil assembly during a bonding process. The bonding process may include applying heat and pressure to the airfoil assembly. A surface of the mold tool may complement a preselected airfoil parameter. The mold tool may maintain the airfoil assembly in the preselected airfoil parameter during the application of heat and pressure to the airfoil assembly.Type: ApplicationFiled: May 17, 2018Publication date: November 21, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, JR., Carney R. Anderson, Peter T. Schutte
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Patent number: 10428684Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.Type: GrantFiled: January 9, 2015Date of Patent: October 1, 2019Assignee: United Technologies CorporationInventor: Thomas J. Robertson, Jr.
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Patent number: 10221718Abstract: A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, and integrated therewith.Type: GrantFiled: August 15, 2014Date of Patent: March 5, 2019Assignee: United Technologies CorporationInventors: Steven C. Clarkson, Thomas J. Robertson, Jr., Michael Parkin
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Publication number: 20180171826Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.Type: ApplicationFiled: February 5, 2018Publication date: June 21, 2018Inventors: Thomas J. Robertson, JR., Mark W. Costa, Steven Clarkson
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Publication number: 20180100408Abstract: A case for a gas turbine engine includes a plurality of distinct case sections in axial series. The case sections include, in axial order, a flange section, a forward shell section, a containment section, and an aft shell section. The forward shell section, the containment section, and the aft shell section are formed of a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. The flange section is formed of a second plurality of non-crimp fabric layers. The plurality of unidirectional roving fiber layers do not have stitching or weaves. A ballistic liner is attached with the containment section, and a fiberglass layer encapsulates the plurality of unidirectional roving fiber layers, the plurality of non-crimp fabric layers, and the second plurality of non-crimp fabric layers.Type: ApplicationFiled: December 8, 2017Publication date: April 12, 2018Inventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, JR., Christopher M. Quinn
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Patent number: 9915168Abstract: A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto.Type: GrantFiled: June 2, 2015Date of Patent: March 13, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Steven Clarkson
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Patent number: 9909458Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.Type: GrantFiled: February 4, 2015Date of Patent: March 6, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Mark W. Costa, Steven Clarkson
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Patent number: 9840936Abstract: A case for a gas turbine engine includes a containment section with a plurality of unidirectional roving fiber layers and a plurality of non-crimp fabric layers. A method of manufacturing the case includes winding the plurality of unidirectional roving fiber layers around the plurality of non-crimp fabric layers.Type: GrantFiled: February 16, 2012Date of Patent: December 12, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Darin S. Lussier, Sreenivasa R. Voleti, Thomas J. Robertson, Jr., Christopher M. Quinn
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Patent number: 9822665Abstract: A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.Type: GrantFiled: December 4, 2014Date of Patent: November 21, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Steven Clarkson
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Patent number: 9702375Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.Type: GrantFiled: July 2, 2014Date of Patent: July 11, 2017Assignee: United Technologies CorporationInventors: Mark W. Costa, Thomas J. Robertson, Jr., David A. Welch
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Patent number: 9651059Abstract: A section of a gas turbine engine includes a case structure and a liner. The liner is attached to the case structure by a compliant adhesive. The adhesive covers at least a portion of the liner surface area, and can have interruptions used to tune the compliance of the adhesive layer.Type: GrantFiled: December 27, 2012Date of Patent: May 16, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Jr., Darin S. Lussier, Kirk D. Stackhouse, Johan Santana
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Publication number: 20160341068Abstract: A fixed-variable vane assembly includes a vane that has a fixed airfoil section and a variable airfoil section next to the fixed airfoil section. The variable airfoil section is pivotably mounted at an end thereof in a joint with a variable joint gap that controls a size of an airfoil gap between the fixed airfoil section and the variable airfoil section. A potting material is located in the variable joint gap. The potting material locks the variable joint gap and locks in the size of the airfoil gap.Type: ApplicationFiled: October 12, 2015Publication date: November 24, 2016Inventors: Thomas J. Robertson, JR., Enzo DiBenedetto, Nathan F. Champion, Niloofar Haghbin, Barry William Spaulding, III
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Publication number: 20160333733Abstract: A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.Type: ApplicationFiled: January 9, 2015Publication date: November 17, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Thomas J. Robertson, JR.
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Patent number: 9482111Abstract: A fan section of a gas turbine engine includes a fan containment case assembly includes an outer case of an aluminum alloy. The outer case extends circumferentially around an axial centerline. A thermally conforming liner assembly is located inwardly of the outer case. The thermally conforming liner assembly includes a circumferential liner of an aluminum alloy. A ballistic liner is located between the outer case and the thermally conforming liner assembly.Type: GrantFiled: December 14, 2012Date of Patent: November 1, 2016Assignee: United Technologies CorporationInventors: Mark W. Costa, Thomas J. Robertson, Jr., Darin S. Lussier