Patents by Inventor Mark W. Costa
Mark W. Costa 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: 20240140083Abstract: A method for preparing an abradable panel for a rub strip of a fan case of a gas turbine engine includes forming an abradable material into a plurality of panels each comprising an abradable structure; curing the abradable material in the plurality of panels; and installing the plurality of panels into the fan case. The panels can be cured and assembled into a fully assembled rubstrip, and then the assembled rubstrip can be installed into the fan case.Type: ApplicationFiled: October 28, 2022Publication date: May 2, 2024Applicant: Raytheon Technologies CorporationInventors: Kerry E. Muenchow, Georgios S. Zafiris, John Harner, Raymond P. Martina, Jr., Imad Hanhan, Darin S. Lussier, Mark W. Costa, Michael R. LaFavor, Scott A. Smith
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Patent number: 11939871Abstract: An abradable material for a rub strip of a gas turbine engine component includes a polymer matrix, and an organic or inorganic filler distributed through the matrix, wherein the abradable material has a compression spring rate profile including: less than 50,000 lb/in at ?65° F., less than 35,000 lb/in at room temperature, and less than 35,000 lb/in at 200° F.Type: GrantFiled: October 28, 2022Date of Patent: March 26, 2024Assignee: RTX CorporationInventors: Kerry E. Muenchow, Georgios S. Zafiris, Raymond P. Martina, Jr., John Harner, Imad Hanhan, Darin S. Lussier, Scott A. Smith, Mark W. Costa, Michael R. LaFavor
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Patent number: 11236769Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.Type: GrantFiled: August 29, 2019Date of Patent: February 1, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Mark W. Costa
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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: 10724403Abstract: A fan case assembly for a gas turbine engine includes a honeycomb structure. The fan case assembly also includes a septum operatively coupled to the honeycomb structure and located radially inward of the honeycomb structure. The fan case assembly further includes a rubstrip in contact with the septum and located radially inward of the septum.Type: GrantFiled: July 16, 2018Date of Patent: July 28, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Mark W. Costa
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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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Publication number: 20200018185Abstract: A fan case assembly for a gas turbine engine includes a honeycomb structure. The fan case assembly also includes a septum operatively coupled to the honeycomb structure and located radially inward of the honeycomb structure. The fan case assembly further includes a rubstrip in contact with the septum and located radially inward of the septum.Type: ApplicationFiled: July 16, 2018Publication date: January 16, 2020Inventor: Mark W. Costa
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Patent number: 10533450Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.Type: GrantFiled: October 30, 2017Date of Patent: January 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Colin J. Kling, Darin S. Lussier, Mark W. Costa
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Publication number: 20200011348Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.Type: ApplicationFiled: August 29, 2019Publication date: January 9, 2020Inventors: Thomas J. Robertson, Mark W. Costa
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Patent number: 10502235Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.Type: GrantFiled: August 22, 2014Date of Patent: December 10, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Mark W. Costa
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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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Patent number: 10480530Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.Type: GrantFiled: August 25, 2017Date of Patent: November 19, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Mark W. Costa
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Patent number: 10436612Abstract: A capacitance probe monitors the distance between a blade tip and a fan, compressor or turbine case. The capacitance probe may be attached to a liner, and may travel with the liner as it radially expands due to thermal changes. The capacitance probe may include a circuit board sensor with a metallic plate, and one or more capacitors. The metallic plate may be encapsulated within an insulating material. A plurality of soft leads may be in electrical communication with the circuit board sensor, allowing a lower lead weight, reduced size and increased flexibility. The soft leads may also be embedded in the liner. In this way, the capacitance probe can record more accurate distance measurements and promote a gas turbine engine's continued and efficient operation.Type: GrantFiled: October 21, 2015Date of Patent: October 8, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Kevin Ford, Eli Warren, Corey A. Benoit, Edward F Dreger, Erik D. Rice, Mark W. Costa
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Publication number: 20190128136Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.Type: ApplicationFiled: October 30, 2017Publication date: May 2, 2019Inventors: Colin J. Kling, Darin S. Lussier, Mark W. Costa
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Publication number: 20190063460Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan containment case assembly that has an outer case extending about an axis, and a thermally conforming liner assembly radially inward of the outer case. The liner assembly has a shell, a wrap radially outward of the shell, and a ballistic liner between the outer case and the wrap. The wrap has a first fiber construction, and the ballistic liner has a second fiber construction that differs from the first fiber construction in stiffness.Type: ApplicationFiled: August 25, 2017Publication date: February 28, 2019Inventor: Mark W. Costa
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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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Patent number: 9982605Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.Type: GrantFiled: September 13, 2013Date of Patent: May 29, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas J. Robertson, Steven Clarkson, Mark w. Costa
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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: 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: 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