Patents by Inventor Carney R. Anderson
Carney R. Anderson 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: 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: 10502230Abstract: An integrally bladed rotor according to an example of the present disclosure includes a hub, and a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub. Each rotor airfoil has a main body that extends radially outward from a root to a tip. A first fillet has a first radius that provides a transition from the outer platform of the hub, and a second fillet situated adjacent to and radially outward of the first fillet, that provides a transition between the first fillet and the main body. The second fillet has a second radius that is less than the first radius.Type: GrantFiled: July 18, 2017Date of Patent: December 10, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Carney R. Anderson
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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: 10458244Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.Type: GrantFiled: October 18, 2017Date of Patent: October 29, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Peter V. Tomeo, Carney R. Anderson
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Publication number: 20190112928Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.Type: ApplicationFiled: October 18, 2017Publication date: April 18, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: PETER V. TOMEO, CARNEY R. ANDERSON
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Patent number: 10260350Abstract: An airfoil structure includes an airfoil that has a leading edge and a platform that includes a first side that is attached to the airfoil and a second side opposite the airfoil. The platform includes a relief cut on the second side of the platform axially aligned with the leading edge.Type: GrantFiled: August 21, 2015Date of Patent: April 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Carney R. Anderson, William R. Graves
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Publication number: 20190024673Abstract: An integrally bladed rotor according to an example of the present disclosure includes a hub, and a plurality of rotor airfoils integrally formed with the hub, and extending radially outward from an outer platform of the hub. Each rotor airfoil has a main body that extends radially outward from a root to a tip. A first fillet has a first radius that provides a transition from the outer platform of the hub, and a second fillet situated adjacent to and radially outward of the first fillet, that provides a transition between the first fillet and the main body. The second fillet has a second radius that is less than the first radius.Type: ApplicationFiled: July 18, 2017Publication date: January 24, 2019Inventor: Carney R. Anderson
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Patent number: 10132174Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.Type: GrantFiled: April 13, 2015Date of Patent: November 20, 2018Assignee: United Technologies CorporationInventors: Colin J. Kling, Thomas J. Robertson, Carney R. Anderson, James J. McPhail
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Patent number: 10072509Abstract: A fan section for a gas turbine engine includes a fan hub having blade slots for receiving a root of a fan blade. A lock ring is configured to move rotatably from an unlocked position to a locked position for securing the blade root in the blade slot. A nose cone is secured to the lock ring, and thereby secured to the fan section.Type: GrantFiled: February 26, 2014Date of Patent: September 11, 2018Assignee: United Technologies CorporationInventors: Corey L. Hubbert, Peter V. Tomeo, Carney R. Anderson
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Patent number: 10066502Abstract: A rotor disk includes a ring shaped rotor body defining a radially inward opening, rims protrude radially outward from the rotor body, and outwardly facing rotor blade retention slots are defined between circumferentially adjacent rims. Each slot is operable to receive and retain a corresponding rotor blade, and each rim of the rims includes an anti-vibratory feature. The anti-vibratory feature includes a structure defining an isogrid pattern intruding into a surface of the rim.Type: GrantFiled: October 21, 2015Date of Patent: September 4, 2018Assignee: United Technologies CorporationInventor: Carney R. Anderson
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Patent number: 9790803Abstract: A rotor assembly for a gas turbine engine includes a plurality of blades including a root portion and an airfoil portion. The rotor includes a plurality of slots that receive the root portion of a corresponding blade. The rotor includes an annular groove for a first and second retaining ring. The retaining rings are received within a common annular groove for holding each of the plurality of blades within the slots of the rotor.Type: GrantFiled: February 21, 2014Date of Patent: October 17, 2017Assignee: United Technologies CorporationInventors: Carney R. Anderson, Peter V. Tomeo
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Patent number: 9682450Abstract: A gas turbine engine fan section includes a fan hub configured to rotate about an axis. A nose cone includes a spinner operatively mounted to the fan hub. The spinner supports a first fastening element and the nose cone includes an annular cover arranged over the fastening element. The spinner and annular cover provide an aerodynamic exterior surface of the nose cone without exposed fasteners. A second fastening element cooperates with the first fastening element to secure the spinner relative to the fan hub. The first and second fastening elements are oriented transversely to the axis.Type: GrantFiled: January 11, 2013Date of Patent: June 20, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Peter V. Tomeo, Carney R. Anderson
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Patent number: 9678098Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.Type: GrantFiled: July 7, 2016Date of Patent: June 13, 2017Assignee: United Technologies CorporationInventors: James Cosby, Peter V. Tomeo, Angel L. Santiago, Carney R. Anderson, Heriberto Rodriguez
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Publication number: 20160313363Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.Type: ApplicationFiled: July 7, 2016Publication date: October 27, 2016Inventors: James Cosby, Peter V. Tomeo, Angel L. Santiago, Carney R. Anderson, Heriberto Rodriguez
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Publication number: 20160298469Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.Type: ApplicationFiled: April 13, 2015Publication date: October 13, 2016Applicant: United Technologies CorporationInventors: Colin J. Kling, Thomas J. Robertson, Carney R. Anderson, James J. McPhail
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Patent number: 9422066Abstract: A grounding sleeve for grounding an electrically insulated element disposed between two metal components includes an annular body extending between a first end and a second end. At least one window is formed in the annular body between the first end and the second end.Type: GrantFiled: March 10, 2014Date of Patent: August 23, 2016Assignee: United Technologies CorporationInventors: Carney R. Anderson, John C. Ditomasso
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Patent number: 9417258Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.Type: GrantFiled: September 10, 2012Date of Patent: August 16, 2016Assignee: United Technologies CorporationInventors: James Cosby, Peter V. Tomeo, Angel L. Santiago, Heriberto Rodriguez, Carney R. Anderson
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Patent number: 9376926Abstract: A gas turbine engine fan blade lock assembly includes a fan hub that has blade slots each configured to receive a root of a fan blade. The fan hub includes circumferentially spaced first slots. A lock ring is configured to move between unlocked and locked positions. The lock ring includes circumferentially spaced second slots aligned with the first slots in the locked position, and multiple discrete pins. Each pin is configured to be slidably received in paired first and second slots in the locked position to prevent rotational movement of the lock ring relative the fan hub.Type: GrantFiled: November 15, 2012Date of Patent: June 28, 2016Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Carney R. Anderson, Peter V. Tomeo
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Patent number: 9366145Abstract: A turbine engine rotor assembly includes a turbine engine rotor disk that extends axially along a centerline between a first disk end and a second disk end, and radially to an outer disk surface. The rotor disk includes one or more blade retention slots arranged circumferentially around the centerline. A first of the blade retention slots extends axially into the rotor disk from a disk end surface at the first disk end to a slot end surface, and radially into the rotor disk from the outer disk surface to a slot base surface.Type: GrantFiled: August 24, 2012Date of Patent: June 14, 2016Assignee: United Technologies CorporationInventors: Peter V. Tomeo, Carney R. Anderson, William Richard Ganoe
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Publication number: 20160115821Abstract: A rotor disk includes a ring shaped rotor body defining a radially inward opening, rims protrude radially outward from the rotor body, and outwardly facing rotor blade retention slots are defined between circumferentially adjacent rims. Each slot is operable to receive and retain a corresponding rotor blade, and each rim of the rims includes an anti-vibratory feature. The anti-vibratory feature includes a structure defining an isogrid pattern intruding into a surface of the rim.Type: ApplicationFiled: October 21, 2015Publication date: April 28, 2016Inventor: Carney R. Anderson