Patents by Inventor Steve Halfmann
Steve Halfmann 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: 20140083116Abstract: A turbine rotor blade for a turbine section of an engine is provided. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path of the turbine section. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, and a tip cap extending between the suction side wall and the pressure side wall. The rotor blade further includes an internal cooling circuit having a tip cap passage configured to deliver cooling air to the tip cap and a flow accelerator positioned within the tip cap passage of the internal cooling circuit.Type: ApplicationFiled: September 27, 2012Publication date: March 27, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Daniel Cregg Crites, Steve Halfmann, Mark C. Morris, Ardeshir Riahi
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Patent number: 8636470Abstract: A turbine blade includes an airfoil defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the interior including an airfoil cooling circuit for directing airflow through the blade, and a platform supporting the airfoil and having a leading side edge, a trailing side edge, suction side edge, a pressure side edge, an airfoil-facing wall, and a root-facing wall, the platform including a platform cooling circuit having an inlet on the leading side edge and an outlet. The turbine blade may be included in a turbine rotor assembly.Type: GrantFiled: October 13, 2010Date of Patent: January 28, 2014Assignee: Honeywell International Inc.Inventors: Steve Halfmann, Mark C. Morris
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Publication number: 20130243606Abstract: A turbine blade includes a blade portion, the blade portion comprising a tip outer wall and a trailing edge, an internal cooling circuit, the internal cooling circuit being configured for directing cooling air within the blade portion, and a tip trailing edge slot positioned adjacent to the tip outer wall and the trailing edge, the tip trailing edge slot being fluidly connected to the internal cooling circuit. The tip outer wall is recessed at the tip trailing edge slot such that the tip outer wall is not provided over the trailing edge slot, thereby allowing cooling air to flow from the cooling circuit, into the trailing edge slot, and radially over the tip outer wall.Type: ApplicationFiled: March 14, 2012Publication date: September 19, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Daniel Cregg Crites, Mark C. Morris, Steve Halfmann
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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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Publication number: 20120148406Abstract: A turbine rotor disk is provided. The turbine rotor disk includes a hub, a ring attached to the hub, the ring including a plurality of posts extending radially outwardly and disposed around a circumference of the ring, each post including a first radially-extending face, a second radially-extending face, and a blade attachment surface extending axially between the first and second radially-extending faces, a main cooling air feed channel formed in each post and extending from the first radially-extending face toward the second radially-extending face, and a plurality of ancillary jet openings formed in each post and extending from the main cooling air feed channel to the blade attachment surface.Type: ApplicationFiled: December 13, 2010Publication date: June 14, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Steve Halfmann, Daniel Cregg Crites, Malak Fouad Malak, Mark C. Morris, Ardeshir Riahi, Brandan Wakefield
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Publication number: 20120093649Abstract: A turbine blade includes an airfoil defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root, and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the interior including an airfoil cooling circuit for directing airflow through the blade, and a platform supporting the airfoil and having a leading side edge, a trailing side edge, suction side edge, a pressure side edge, an airfoil-facing wall, and a root-facing wall, the platform including a platform cooling circuit having an inlet on the leading side edge and an outlet. The turbine blade may be included in a turbine rotor assembly.Type: ApplicationFiled: October 13, 2010Publication date: April 19, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Steve Halfmann, Mark C. Morris
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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: 20100254807Abstract: A seal plate for a turbine engine is provided. The turbine engine has a central axis. The seal plate comprises a forward face extending radially from the central axis. The forward face comprises a flat portion extending circumferentially around the central axis, and a front flow discourager coupled to the flat portion and extending outward from the flat portion.Type: ApplicationFiled: April 7, 2009Publication date: October 7, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jason Smoke, Steve Halfmann, Brandan Wakefield
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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
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Publication number: 20060078422Abstract: A method of modifying a turbine nozzle area comprises depositing a thermal barrier coating (TBC) on the nozzle endwalls to provide a minimum nozzle area, evaluating an airflow through the nozzle, and machining the TBC to increase the nozzle area. Adjacent segment area variation may be minimized, improving engine reliability by reducing the aerodynamic excitation to the down stream blade.Type: ApplicationFiled: October 12, 2004Publication date: April 13, 2006Applicant: Honeywell International Inc.Inventors: Mark Morris, Thomas Strangman, Craig Wilson, George Wolfmeyer, Steve Halfmann, David Jan
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Publication number: 20060065383Abstract: Methods for rapid prototype casting metal components, wherein the metal components are cast in a secondary ceramic mold, the secondary ceramic mold is cast in a primary mold, and the primary mold is formed by rapid prototyping or rapid manufacturing. The secondary ceramic mold may comprise a one-piece integral shell and core(s), and the metal components may have at least one hollow portion or void therein, such as a hollow airfoil for a gas turbine engine.Type: ApplicationFiled: September 24, 2004Publication date: March 30, 2006Applicant: Honeywell International Inc.Inventors: Milton Ortiz, Malak Malak, Steve Halfmann
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Publication number: 20050129499Abstract: A turbine shroud assembly includes forward and aft hangers, an axisymmetric plenum assembly, ceramic shroud segments, ceramic spacers, and forward and aft rope seals. The plenum assembly supplies impingement cooling to the shroud and the hangers. The impingement cooling to the forward and aft hangers is controlled independently to improve blade tip clearance. The rope seals are radially inward from the hangers and reduce cooling flow leakage. The turbine shroud assembly can operate in a higher temperature environment using less cooling flow than the prior art.Type: ApplicationFiled: December 11, 2003Publication date: June 16, 2005Applicant: Honeywell International Inc.Inventors: Mark Morris, Steve Halfmann, Craig Wilson, Shawn Pollock, Carl Larson