Patents by Inventor Bob Mitlin
Bob Mitlin 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: 9670781Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.Type: GrantFiled: September 17, 2013Date of Patent: June 6, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Steve Halfmann, Mark C. Morris, Jason Smoke, Brandan Wakefield, Bob Mitlin
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Publication number: 20150075178Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.Type: ApplicationFiled: September 17, 2013Publication date: March 19, 2015Inventors: Steve Halfmann, Mark C. Morris, Jason Smoke, Brandan Wakefield, Bob Mitlin
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Patent number: 8616832Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: GrantFiled: November 30, 2009Date of Patent: December 31, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Patent number: 8381533Abstract: An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.Type: GrantFiled: April 30, 2009Date of Patent: February 26, 2013Assignee: Honeywell International Inc.Inventors: Jason Smoke, Bob Mitlin, Alexander MirzaMoghadam
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Patent number: 8297935Abstract: Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.Type: GrantFiled: November 18, 2008Date of Patent: October 30, 2012Assignee: Honeywell International Inc.Inventors: Bob Mitlin, Mark C. Morris, Steve Halfmann, Ardeshir Riahi
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Patent number: 8292587Abstract: A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.Type: GrantFiled: December 18, 2008Date of Patent: October 23, 2012Assignee: Honeywell International Inc.Inventors: Kin Poon, Rajiv Rana, Bob Mitlin, Ardeshir Riahi, David Chou, Steve Halfmann, Frank Mignano
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Patent number: 8147197Abstract: A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.Type: GrantFiled: March 10, 2009Date of Patent: April 3, 2012Assignee: Honeywell International, Inc.Inventors: Mark C. Morris, Jason Smoke, Jeff Howe, Bob Mitlin
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Publication number: 20110129342Abstract: A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.Type: ApplicationFiled: November 30, 2009Publication date: June 2, 2011Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bradley Reed Tucker, Bob Mitlin, Dan Crites, Rajiv Rana, Alexander MirzaMoghadam
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Publication number: 20100284819Abstract: Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.Type: ApplicationFiled: November 18, 2008Publication date: November 11, 2010Applicant: Honeywell International Inc.Inventors: Bob Mitlin, Mark C. Morris, Steve Halfmann, Ardeshir Riahi
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Publication number: 20100275612Abstract: An apparatus for cooling turbine blades in a turbine engine including a direct transfer axial tangential onboard injector (TOBI) for a turbine rotor and a self-supporting seal plate disposed on a rotating disk for the turbine engine. The TOBI includes a plurality of openings emanating a flow of cooling air. The self-supporting seal plate comprises a plurality of shaped cooling holes in fluid communication with the flow of cooling air emanating from the TOBI. The rotating disk includes a plurality of turbine blade slots formed therein. The plurality of cooling holes are in fluid communication with the plurality of turbine blade slots for directing the flow of cooling air to provide cooling to the plurality of turbine blades. The plurality of openings, the plurality of cooling holes and the plurality of turbine blade slots are in axial alignment and optimized to minimize radial and hoop stresses.Type: ApplicationFiled: April 30, 2009Publication date: November 4, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Bob Mitlin, Alexander MirzaMoghadam
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Publication number: 20100232975Abstract: A turbine blade assembly is provided. The turbine blade assembly comprises a turbine blade comprising a cavity, and a blade platform supporting the turbine blade, the cavity extending into the blade platform. The blade platform comprises an upper surface adjacent the turbine blade and a lower surface comprising a first rib, the cavity extending into the first rib, the first rib coupled to the lower surface, tapering as it extends away from the turbine blade, and comprising a first port extending from the cavity to the upper surface.Type: ApplicationFiled: March 10, 2009Publication date: September 16, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Mark C. Morris, Jason Smoke, Jeff Howe, Bob Mitlin
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Publication number: 20100158700Abstract: A turbine blade assembly includes an airfoil, a platform, and a first cover plate. A center flow path extends through the platform in communication with an internal cooling circuit of the airfoil, which extends from a first side of the platform. A second side of the platform is located opposite the platform from the first side. An edge of the platform extends between the first and second sides and, a first passage is formed between the first and second sides and includes a first inlet and a first outlet. The first passage extends from the center flow path toward the platform edge, and a first groove is formed on the second side of the platform and extends from the first outlet of the first passage toward the edge of the platform. The first cover plate is disposed over the second side of the platform covering the first groove.Type: ApplicationFiled: December 18, 2008Publication date: June 24, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Kin Poon, Rajiv Rana, Bob Mitlin, Ardeshir Riahi, David Chou, Steve Halfmann, Frank Mignano