Patents by Inventor John C. DiTomasso
John C. DiTomasso 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: 20230116394Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade.Type: ApplicationFiled: December 7, 2022Publication date: April 13, 2023Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: JOHN C. DITOMASSO, MATTHEW P. FORCIER
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Patent number: 11549518Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.Type: GrantFiled: September 10, 2021Date of Patent: January 10, 2023Assignee: Raytheon Technologies CorporationInventors: John C. Ditomasso, Matthew P. Forcier
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Publication number: 20220106964Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.Type: ApplicationFiled: September 10, 2021Publication date: April 7, 2022Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: JOHN C. DITOMASSO, MATTHEW P. FORCIER
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Patent number: 11215056Abstract: A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.Type: GrantFiled: April 9, 2020Date of Patent: January 4, 2022Assignee: Raytheon Technologies CorporationInventors: Gabriel P. Smith, John C. DiTomasso
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Publication number: 20210317743Abstract: A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.Type: ApplicationFiled: April 9, 2020Publication date: October 14, 2021Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Gabriel P. Smith, John C. DiTomasso
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Patent number: 11136991Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.Type: GrantFiled: May 4, 2020Date of Patent: October 5, 2021Assignee: Raytheon Technologies CorporationInventors: John C. Ditomasso, Matthew P. Forcier
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Patent number: 10935048Abstract: In one exemplary embodiment, a center body support for a gas turbine engine includes a fan exit guide vane mounting ring and an outer annular wall. An aft flange extends radially outward from the outer annular wall. An inner annular wall is radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange includes inner and outer mounting features spaced radially apart from one another. The inner and outer mounting feature respectively receive first and second sets of fasteners. The forward portion extends in a radially outward direction from the outer annular wall. The forward portion includes a forward mounting feature that receives a third set of fasteners. The outer and forward mounting features are secured to the fan exit guide vane mounting ring respectively by the first and third sets of fasteners.Type: GrantFiled: October 15, 2018Date of Patent: March 2, 2021Assignee: Raytheon Technologies CorporationInventors: John C. Ditomasso, Gregory E. Reinhardt
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Patent number: 10927686Abstract: A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.Type: GrantFiled: March 6, 2020Date of Patent: February 23, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: John C. DiTomasso
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Publication number: 20200392967Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.Type: ApplicationFiled: May 4, 2020Publication date: December 17, 2020Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: JOHN C. DITOMASSO, MATTHEW P. FORCIER
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Patent number: 10830087Abstract: A modular variable vane assembly includes an airfoil, an inner case, and an outer case. The airfoil extends between a first end and a second end along an axis. The airfoil has a connector that extends from the first end and a pivot member that extends from the second end. The inner case defines a pivot opening that is arranged to receive the pivot member. The outer case defines a first opening that extends from a first outer case surface towards a second outer case surface along the axis. The first opening is arranged to receive the connector.Type: GrantFiled: December 10, 2018Date of Patent: November 10, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Jonathon T. Pacuk, John C. Ditomasso
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Publication number: 20200208531Abstract: A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.Type: ApplicationFiled: March 6, 2020Publication date: July 2, 2020Inventor: John C. DiTomasso
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Publication number: 20200182082Abstract: A modular variable vane assembly includes an airfoil, an inner case, and an outer case. The airfoil extends between a first end and a second end along an axis. The airfoil has a connector that extends from the first end and a pivot member that extends from the second end. The inner case defines a pivot opening that is arranged to receive the pivot member. The outer case defines a first opening that extends from a first outer case surface towards a second outer case surface along the axis. The first opening is arranged to receive the connector.Type: ApplicationFiled: December 10, 2018Publication date: June 11, 2020Inventors: Jonathon T. Pacuk, John C. Ditomasso
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Patent number: 10619649Abstract: A bellcrank assembly for variable vane assembly of a gas turbine engine includes a first bellcrank segment. Also included is a second bellcrank segment. Further included is a bolt extending through respective interior barrels defined by the first and second bellcrank segments to couple the first and second bellcrank segments to each other. Yet further included is a torque frame wall defining an aperture, the bolt extending through the aperture.Type: GrantFiled: April 4, 2017Date of Patent: April 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: William S. Pratt, John C. DiTomasso
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Patent number: 10584599Abstract: A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.Type: GrantFiled: July 14, 2017Date of Patent: March 10, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: John C. DiTomasso
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Patent number: 10473028Abstract: A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.Type: GrantFiled: July 17, 2017Date of Patent: November 12, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John C. DiTomasso, Enzo DiBenedetto
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Publication number: 20190107120Abstract: In one exemplary embodiment, a center body support for a gas turbine engine includes a fan exit guide vane mounting ring and an outer annular wall. An aft flange extends radially outward from the outer annular wall. An inner annular wall is radially spaced from and structurally interconnected to the outer annular wall by a circumferential array of struts. A brace interconnects the aft flange to a forward portion of the outer annular wall. The aft flange includes inner and outer mounting features spaced radially apart from one another. The inner and outer mounting feature respectively receive first and second sets of fasteners. The forward portion extends in a radially outward direction from the outer annular wall. The forward portion includes a forward mounting feature that receives a third set of fasteners. The outer and forward mounting features are secured to the fan exit guide vane mounting ring respectively by the first and third sets of fasteners.Type: ApplicationFiled: October 15, 2018Publication date: April 11, 2019Inventors: John C. Ditomasso, Gregory E. Reinhardt
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Patent number: 10233841Abstract: In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.Type: GrantFiled: November 5, 2015Date of Patent: March 19, 2019Assignee: United Technologies CorporationInventors: Matthew E. Bintz, Charles P. Gendrich, John C. DiTomasso, Andrew J. Murphy
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Publication number: 20190017516Abstract: A compressor rotor assembly including a plurality of rotor disks axially spaced from each other, each rotor disk extending radially from an inner end to an outer end. Also included is a spacer extending axially from each rotor disk to engage an adjacent spacer extending from an adjacent rotor disk, the spacer and adjacent spacer disposed proximate the outer end of the respective rotor disks, the spacers forming an outer backbone of the compressor rotor assembly. Further included is an inner backbone of the compressor rotor assembly, the inner backbone comprising a plurality of backbone segments, each of the backbone segments extending axially from each rotor disk to engage an adjacent backbone segment extending from an adjacent rotor disk, the backbone segment and the adjacent backbone segment disposed proximate the inner end of the respective rotor disks.Type: ApplicationFiled: July 14, 2017Publication date: January 17, 2019Inventor: John C. DiTomasso
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Publication number: 20190017436Abstract: A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.Type: ApplicationFiled: July 17, 2017Publication date: January 17, 2019Inventors: John C. DiTomasso, Enzo DiBenedetto
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Publication number: 20190010956Abstract: A tandem rotor disk apparatus may include a rotor disk body concentric about an axis. The tandem rotor disk apparatus may also include a first blade extending radially outward of the rotor disk body and a second blade extending radially outward of the rotor disk body. The first blade may be offset from the second blade in a direction parallel to the axis. The tandem rotor disk apparatus may be implemented in a gas turbine engine with no intervening stator vane stages disposed between the first blade and the second blade. The tandem rotor disk apparatus may include two separate rotor disk bodies.Type: ApplicationFiled: July 6, 2017Publication date: January 10, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JOHN C. DITOMASSO, MATTHEW P. FORCIER