Patents by Inventor Nicholas Aiello
Nicholas Aiello 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: 10982555Abstract: A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.Type: GrantFiled: February 27, 2014Date of Patent: April 20, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Nicholas Aiello, John C. Duong
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Patent number: 10704401Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.Type: GrantFiled: August 10, 2018Date of Patent: July 7, 2020Assignee: Raytheon Technologies CorporationInventors: Nicholas Aiello, James Cosby
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Patent number: 10648481Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.Type: GrantFiled: November 2, 2015Date of Patent: May 12, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
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Patent number: 10458265Abstract: An integrally bladed rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a radially inner hoop extending circumferentially about an axis, a plurality of circumferentially spaced, axially extending slots, separated by respective blade supports, and a seal system that includes seal fingers extending axially through the slots.Type: GrantFiled: March 19, 2014Date of Patent: October 29, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Nicholas Aiello
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Publication number: 20190316403Abstract: A device for determining the position of a rear door or liftgate of a cargo truck or trailer includes a base attachable to the rear door or liftgate. A visual indicator extends from the base so as to be viewable from a side view mirror of the truck to enable a driver of the truck to determine the position of the rear door or liftgate due to the position of the visual indicator. The visual indicator may be a plurality of closely spaced apart elongated members, which may be brightly colored or light transmissive so as to be easily seen.Type: ApplicationFiled: April 13, 2018Publication date: October 17, 2019Inventor: Nicholas A. Aiello
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Patent number: 10370971Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.Type: GrantFiled: November 2, 2015Date of Patent: August 6, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
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Patent number: 10167729Abstract: A knife edge seal includes a pedestal and a knife edge with a tip and a base. The base rests on the pedestal. The base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1. A gas turbine engine and a method of sealing a high pressure area from a low pressure area are also disclosed.Type: GrantFiled: February 12, 2014Date of Patent: January 1, 2019Assignee: United Technologies CorporationInventors: Nicholas Aiello, Uyen Phan
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Publication number: 20180363480Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.Type: ApplicationFiled: August 10, 2018Publication date: December 20, 2018Inventors: Nicholas Aiello, James Cosby
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Patent number: 10107114Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.Type: GrantFiled: December 7, 2011Date of Patent: October 23, 2018Assignee: United Technologies CorporationInventors: Nicholas Aiello, James Cosby
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Patent number: 10029336Abstract: A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.Type: GrantFiled: November 5, 2015Date of Patent: July 24, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
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Patent number: 9828865Abstract: An example turbomachine rotor provides a groove that is annular and is configured to receive a root of an airfoil, the groove having a radial cross-sectional area. A ratio of the radial cross-sectional area of the groove to a radial cross-sectional area of the root received within the annular groove is from 2 to 5.Type: GrantFiled: September 26, 2012Date of Patent: November 28, 2017Assignee: United Technologies CorporationInventors: Nicholas Aiello, Raji Mali
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Patent number: 9803481Abstract: A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.Type: GrantFiled: June 16, 2015Date of Patent: October 31, 2017Assignee: United Technologies CorporationInventors: Nicholas Aiello, Bob S. Bamford
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Publication number: 20160153463Abstract: A spacer of a gas turbine engine is reinforced with a fiber. The fiber can be cured with a substrate to form a fiber reinforced composite material. As a gas turbine engine operates, the rotation creates forces which can deform, expand, contract or translate certain gas turbine engine components, including spacers. These forces can adversely affect gas turbine engine performance and reliability, particularly when they are either unpredictable or difficult to control. Reinforcing a spacer with a fiber may allow a lower system weight, more compact or configurable internal packaging or a high degree of reinforcement.Type: ApplicationFiled: November 2, 2015Publication date: June 2, 2016Inventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
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Publication number: 20160146023Abstract: A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.Type: ApplicationFiled: November 5, 2015Publication date: May 26, 2016Inventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
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Publication number: 20160138399Abstract: A structurally-reinforced rotor disk for a gas turbine engine is disclosed. The rotor disk may comprise a body including a rim configured to support airfoils (which may be separate or integral with the airfoils), an axially-extending bore disposed radially inward of the rim, and a radially-extending web connecting the rim and the bore. The bore may include an axial outer edge and at least one circumferentially-extending annular recess formed axially between the outer edge and the web. The rotor disk may further comprise an annular ring retained in the annular recess, and the annular ring may be formed from a different material than the body of the rotor disk so as to increase a self-sustaining radius of the rotor disk.Type: ApplicationFiled: November 2, 2015Publication date: May 19, 2016Inventors: Anthony R. Bifulco, Damon K. Brown, Nicholas Aiello
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Patent number: 9341070Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. A load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.Type: GrantFiled: May 30, 2012Date of Patent: May 17, 2016Assignee: United Technologies CorporationInventors: Nicholas Aiello, James Cosby, Kevin L. Corcoran
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Publication number: 20160076386Abstract: A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.Type: ApplicationFiled: February 27, 2014Publication date: March 17, 2016Inventors: Nicholas Aiello, John C. Duong
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Publication number: 20160069203Abstract: An integrally bladed rotor for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a radially inner hoop extending circumferentially about an axis, a plurality of circumferentially spaced, axially extending slots, separated by respective blade supports, and a seal system that includes seal fingers extending axially through the slots.Type: ApplicationFiled: April 12, 2013Publication date: March 10, 2016Inventor: Nicholas Aiello
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Publication number: 20160003076Abstract: A knife edge seal includes a pedestal and a knife edge with a tip and a base. The base rests on the pedestal. The base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1. A gas turbine engine and a method of sealing a high pressure area from a low pressure area are also disclosed.Type: ApplicationFiled: February 12, 2014Publication date: January 7, 2016Inventors: Nicholas Aiello, Uyen Phan
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Publication number: 20150369045Abstract: A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.Type: ApplicationFiled: June 16, 2015Publication date: December 24, 2015Inventors: Nicholas Aiello, Bob S. Bamford