Patents by Inventor Andrew G. Alarcon
Andrew G. Alarcon 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: 10533435Abstract: In a featured embodiment, a fan rotor includes a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.Type: GrantFiled: November 7, 2014Date of Patent: January 14, 2020Assignee: United Technologies CorporationInventors: Charles W. Brown, Andrew G. Alarcon, Shari L. Bugaj, Charles R. Watson
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Patent number: 10344601Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.Type: GrantFiled: March 15, 2013Date of Patent: July 9, 2019Assignee: United Technologies CorporationInventors: Matthew A. Turner, Andrew G. Alarcon, James Glaspey, Brian Green, Barry M. Ford, Renee J. Jurek
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Patent number: 10227884Abstract: A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.Type: GrantFiled: August 6, 2014Date of Patent: March 12, 2019Assignee: United Technologies CorporationInventor: Andrew G. Alarcon
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Publication number: 20180195402Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.Type: ApplicationFiled: December 11, 2014Publication date: July 12, 2018Inventors: Matthew A. Turner, Andrew G. Alarcon, Shari L. Bugaj
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Patent number: 10018048Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.Type: GrantFiled: December 16, 2013Date of Patent: July 10, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Andrew G. Alarcon, Christopher M. Quinn, James Glaspey, Matthew A. Turner
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Publication number: 20170030205Abstract: In a featured embodiment, a fan rotor comprises a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.Type: ApplicationFiled: November 7, 2014Publication date: February 2, 2017Inventors: Charles W. Brown, Andrew G. Alarcon, Shari L. Bugaj, Charles R. Watson
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Publication number: 20160341071Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.Type: ApplicationFiled: December 15, 2014Publication date: November 24, 2016Applicant: United Technologies CorporationInventors: Andrew G. Alarcon, Royce E. Tatton, Barry M. Ford, Linda S. Li, Matthew A. Turner
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Publication number: 20160305439Abstract: An edge seal for preventing airflow through a space between a fan platform and an adjacent airfoil in a gas turbine engine may include a bonding segment being bondable to the fan platform. A sealing flap converges with the bonding segment so that the sealing flap is operatively contactable with the adjacent airfoil. A bumper rib protrudes from the bonding segment so that the bumper rib is bondable to the fan platform.Type: ApplicationFiled: August 15, 2014Publication date: October 20, 2016Inventors: Andrew G. ALARCON, William BOGUE
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Publication number: 20160258319Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber composite inlet guide vane for a gas turbine engine.Type: ApplicationFiled: November 18, 2014Publication date: September 8, 2016Inventors: Matthew A. Turner, Andrew G. Alarcon, Shari L. Bugaj
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Publication number: 20160194973Abstract: A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and between a suction wall and a pressure wall. A circumferential direction is defined between the suction wall and the pressure wall. A tab extend circumferentially outward of one of the suction and pressure walls from the platform. The tab has a circumferentially outermost portion which will abut an inner surface of an adjacent platform when the platform is mounted. A fan section and a gas turbine engine are also disclosed.Type: ApplicationFiled: August 6, 2014Publication date: July 7, 2016Inventor: Andrew G. Alarcon
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Publication number: 20160160680Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber structural guide vane for a gas turbine engine.Type: ApplicationFiled: November 13, 2014Publication date: June 9, 2016Inventors: Matthew A. Turner, Andrew G. Alarcon, Shari L. Bugaj, Glenn Levasseur
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Publication number: 20160153287Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.Type: ApplicationFiled: July 9, 2014Publication date: June 2, 2016Inventors: James T. Roach, Grant O. Cook, Lakshminarayan S. Bettagere, Jonathan F. Zimmitti, Majidullah Dehlavi, Shari L. Bugaj, Charles R. Watson, Brian D. Walter, Andrew G. Alarcon, Sarah M. Wall, Christopher J. Hertel, Octavio Martin, Thomas J. Robertson, Aaron Beaudry, Jeffrey J. Scalia, Joseph J. Wassel, Joe Ott, Barry Barnett, Glenn Levasseur
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Patent number: 9297268Abstract: A seal for sealing a gap between adjacent first and second components, includes a first portion for attaching to the first component and a second portion extending at an angle from the first portion, the second portion having a top extending therealong that is flat in an uninstalled position, a thickened portion beneath the top and a hinge wherein the thickened portion is disposed between the hinge and an end of the top.Type: GrantFiled: September 6, 2012Date of Patent: March 29, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Andrew G. Alarcon
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Patent number: 9267386Abstract: A fairing assembly includes an outer wall, a first side wall, a second side wall, and a saddle. The first side wall and the second side wall extend from opposing sides of the outer wall. Together the first side wall, the second side wall, and the outer wall form a cavity within the fairing assembly. The saddle is positioned within the cavity and extends between the first side wall and the second side wall. The saddle has a first rib adapted to connect to the first side wall and a second rib adapted to connect to the second side wall. The first rib and the second rib connect together at a central hub.Type: GrantFiled: June 29, 2012Date of Patent: February 23, 2016Assignee: United Technologies CorporationInventors: Matthew A. Turner, Charles W. Brown, Shari L. Bugaj, Christopher M. Quinn, David J. Hyland, Andrew G. Alarcon
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Publication number: 20150337661Abstract: Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.Type: ApplicationFiled: December 16, 2013Publication date: November 26, 2015Inventors: Andrew G. Alarcon, Christopher M. Quinn, James Glaspey, Matthew A. Turner
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Patent number: 9194299Abstract: An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes the amount of machining that must be done prior to assembly. The anti-torsion assembly comprises a torque block with outwardly-opposing side surfaces and a pair of L-brackets. Each L-bracket has a bracket surface that faces one of the outwardly-opposing side surfaces of the torque block. A wear pad is affixed to each bracket surface. The L-brackets are positioned onto the thermally conforming liner using a spacer having a spacer width within a predetermined tolerance. A method of assembling a fan case assembly is also provided.Type: GrantFiled: December 21, 2012Date of Patent: November 24, 2015Assignee: United Technologies CorporationInventor: Andrew G. Alarcon
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Publication number: 20150330255Abstract: An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes relative movement of the thermally conforming liner and the fan containment case by providing a wedge shaped torque block and complimentary shaped L-brackets. A method of assembling a fan case assembly is also provided.Type: ApplicationFiled: December 13, 2013Publication date: November 19, 2015Inventor: Andrew G. Alarcon
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Publication number: 20150204201Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.Type: ApplicationFiled: March 15, 2013Publication date: July 23, 2015Inventors: Matthew A. Turner, Andrew G. Alarcon, James Glaspey, Brian Green, Barry M. Ford, Renee J. Jurek
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Publication number: 20150117804Abstract: A gas turbine engine bushing includes a flange area, and an insert area to be received within an aperture. The insert area includes channels and a bond rib. The channels extend axially a channel distance. The bond rib extends axially a bond rib distance. The channel distance is eater than the bond rib distance.Type: ApplicationFiled: October 24, 2014Publication date: April 30, 2015Inventor: Andrew G. Alarcon
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Publication number: 20140173897Abstract: An anti-torsion assembly for positioning and securing a thermally conforming liner within a fan containment case is provided. The anti-torsion assembly minimizes the amount of machining that must be done prior to assembly. The anti-torsion assembly comprises a torque block with outwardly-opposing side surfaces and a pair of L-brackets. Each L-bracket has a bracket surface that faces one of the outwardly-opposing side surfaces of the torque block. A wear pad is affixed to each bracket surface. The L-brackets are positioned onto the thermally conforming liner using a spacer having a spacer width within a predetermined tolerance. A method of assembling a fan case assembly is also provided.Type: ApplicationFiled: December 21, 2012Publication date: June 26, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Andrew G. Alarcon