Patents by Inventor Norman A. Pietruska
Norman A. Pietruska 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: 20150167125Abstract: A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.Type: ApplicationFiled: February 27, 2015Publication date: June 18, 2015Inventors: Beth Kwiatkowski Abriles, Norman Pietruska, John H. Hyde
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Patent number: 8999231Abstract: A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.Type: GrantFiled: May 24, 2006Date of Patent: April 7, 2015Assignee: United Technologies CorporationInventors: Beth Kwiatkowski Abriles, Norman Pietruska, John H. Hyde
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Patent number: 8353444Abstract: The present invention is directed to a process for repairing cracks in a turbine engine component. The process comprises the steps of providing a component, preferably formed from a single crystal nickel based material, with at least one crack, applying a repair alloy composition containing a single crystal nickel based alloy, a first nickel based braze alloy and a second nickel based braze alloy to the crack(s), and subjecting the component with the applied repair alloy composition to a thermal cycle to diffuse the repair alloy composition into the crack(s).Type: GrantFiled: October 28, 2005Date of Patent: January 15, 2013Assignee: United Technologies CorporationInventors: Norman Pietruska, Beth Kwiatkowski Abriles, John F. Falkowski
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Patent number: 8067711Abstract: Microspray apparatus and methods involve injecting powdered material into a plasma gas stream. The material comprises first and second component powders. The second powder is a majority by the weight of the powdered material. The first powder acts as a melting point depressant. The first and second powders may have similar compositions but with the first powder including a greater quantity of a melting point depressant element.Type: GrantFiled: July 14, 2005Date of Patent: November 29, 2011Assignee: United Technologies CorporationInventors: Donn R. Blankenship, David A. Rutz, Norman A. Pietruska, Paul H. Zajchowski, Gary Shubert
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Patent number: 7966707Abstract: A method for forming or remanufacturing a component to have an internal space. A refractory metal blocking element is formed, in situ, with at least a portion to be within the internal space. A material is added by at least one of welding, laser cladding, and diffusion brazing, the blocking element at least partially blocking entry of the material to the internal space. The blocking element is removed.Type: GrantFiled: May 6, 2005Date of Patent: June 28, 2011Assignee: United Technologies CorporationInventors: Edward R. Szela, Norman Pietruska
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Publication number: 20100096368Abstract: Microspray apparatus and methods involve injecting powdered material into a plasma gas stream. The material comprises first and second component powders. The second powder is a majority by the weight of the powdered material. The first powder acts as a melting point depressant. The first and second powders may have similar compositions but with the first powder including a greater quantity of a melting point depressant element.Type: ApplicationFiled: July 14, 2005Publication date: April 22, 2010Inventors: Donn R. Blankenship, David A. Rutz, Norman A. Pietruska, Paul H. Zajchowski, Gary Shubert
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Patent number: 7360678Abstract: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.Type: GrantFiled: January 27, 2005Date of Patent: April 22, 2008Assignee: United Technologies CorporationInventors: Norman Pietruska, Walter E. Olson, Beth K. Abriles, David A. Rutz
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Publication number: 20070272332Abstract: A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.Type: ApplicationFiled: May 24, 2006Publication date: November 29, 2007Inventors: Beth Kwiatkowki Abriles, Norman Pietruska, John H. Hyde
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Publication number: 20070102483Abstract: The present invention is directed to a process for repairing cracks in a turbine engine component. The process comprises the steps of providing a component, preferably formed from a single crystal nickel based material, with at least one crack, applying a repair alloy composition containing a single crystal nickel based alloy, a first nickel based braze alloy and a second nickel based braze alloy to the crack(s), and subjecting the component with the applied repair alloy composition to a thermal cycle to diffuse the repair alloy composition into the crack(s).Type: ApplicationFiled: October 28, 2005Publication date: May 10, 2007Inventors: Norman Pietruska, Beth Abriles, John Falkowski
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Publication number: 20060248719Abstract: A method for forming or remanufacturing a component to have an internal space. A refractory metal blocking element is formed, in situ, with at least a portion to be within the internal space. A material is added by at least one of welding, laser cladding, and diffusion brazing, the blocking element at least partially blocking entry of the material to the internal space. The blocking element is removed.Type: ApplicationFiled: May 6, 2005Publication date: November 9, 2006Inventors: Edward Szela, Norman Pietruska
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Publication number: 20060163323Abstract: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.Type: ApplicationFiled: January 27, 2005Publication date: July 27, 2006Inventors: Norman Pietruska, Walter Olson, Beth Abriles, David Rutz
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Patent number: 6742698Abstract: The present invention relates to a method for repairing components such as blades used in turbine engines. The method comprises the steps of placing a piece of refractory metal material over an area of the component to be repaired and depositing a repair filler metal material over the piece of refractory material in an amount sufficient to repair the component and welding the repair filler metal material in place. The refractory metal material may be selected from the group consisting of niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than the melting point of nickel, and alloys thereof and may be uncoated or coated.Type: GrantFiled: June 10, 2002Date of Patent: June 1, 2004Assignee: United Technologies CorporationInventors: Dilip M. Shah, James T. Beals, Norman Pietruska, Edward R. Szela
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Patent number: 6725540Abstract: The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.Type: GrantFiled: March 9, 2002Date of Patent: April 27, 2004Assignee: United Technologies CorporationInventors: Sudhangshu Bose, Alan D. Cetel, Peter J. Draghi, Norman Pietruska
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Publication number: 20030226878Abstract: The present invention relates to a method for repairing components such as blades used in turbine engines. The method comprises the steps of placing a piece of refractory metal material over an area of the component to be repaired and depositing a repair filler metal material over the piece of refractory material in an amount sufficient to repair the component and welding the repair filler metal material in place. The refractory metal material may be selected from the group consisting of niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than the melting point of nickel, and alloys thereof and may be uncoated or coated.Type: ApplicationFiled: June 10, 2002Publication date: December 11, 2003Inventors: Dilip M. Shah, James T. Beals, Norman Pietruska, Edward R. Szela
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Publication number: 20030167636Abstract: The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.Type: ApplicationFiled: March 9, 2002Publication date: September 11, 2003Inventors: Sudhangshu Bose, Alan D. Cetel, Peter J. Draghi, Norman Pietruska
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Patent number: 6503349Abstract: The present invention relates to a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment.Type: GrantFiled: May 15, 2001Date of Patent: January 7, 2003Assignee: United Technologies CorporationInventors: Norman Pietruska, David J. Kline
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Publication number: 20020185198Abstract: The present invention relates to a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment.Type: ApplicationFiled: May 15, 2001Publication date: December 12, 2002Inventors: Norman Pietruska, David J. Kline
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Patent number: 6045863Abstract: The invention includes a low activity localized aluminide coating for a metallic article made by positioning a coating material, preferably in the form of a tape, on a portion of the article. The coating material comprises a binder, a halide activator, an aluminum source, and an inert ceramic material. The coating material and the article are heated in an inert atmosphere between about 1800.degree. F. (982.degree. C.) and about 2050.degree. F. (1121.degree. C.) for between about four and about seven hours thereby producing a low activity localized aluminide coating having an outward diffusion aluminide coating microstructure characterized by two distinct zones, an inner diffusion zone and an outer zone including between about 20-28 percent, by weight, aluminum.Type: GrantFiled: November 18, 1997Date of Patent: April 4, 2000Assignee: United Technologies CompanyInventors: Walter E. Olson, Norman Pietruska, Peter Jon Draghi
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Patent number: 6022632Abstract: The invention includes a low activity localized aluminide coating for a metallic article made by positioning a coating material, preferably in the form of a tape, on a portion of the article. The coating material comprises a binder, a halide activator, an aluminum source, and an inert ceramic material. The coating material and the article are heated in an inert atmosphere between about 1800.degree. F. (982.degree. C.) and about 2050.degree. F. (1121.degree. C.) for between about four and about seven hours thereby producing a low activity localized aluminide coating having an outward diffusion aluminide coating microstructure characterized by two distinct zones, an inner diffusion zone and an outer zone including between about 20-28 percent, by weight, aluminum.Type: GrantFiled: October 18, 1996Date of Patent: February 8, 2000Assignee: United TechnologiesInventors: Walter E. Olson, Norman Pietruska, Peter Jon Draghi
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Patent number: 5922150Abstract: An improved method is described for repairing Co-base superalloy gas turbine engine components by applying a mixture of base alloy powder and base alloy powder with a melting point depressant to the surface of the component and heating at 2250-2300.degree. F. to diffuse the melting point depressant isothermally into the base alloy. A protective coating is then applied, during which a heating cycle which ages the base material is used. The resultant component has high temperature creep properties which are significantly better than achieved using the prior art process. The same temperature cycle is also useful in the initial heat treatment of Co-base superalloys, and can also be used for rejuvenation of components which have experienced extensive exposure to engine operating conditions.Type: GrantFiled: December 16, 1997Date of Patent: July 13, 1999Assignee: United Technologies CorporationInventors: Norman Pietruska, S. Michael Kurpaska