Patents by Inventor John F. Ackermann
John F. Ackermann 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: 11594308Abstract: Methods and systems providing adaptive assessment of a physical subject to efficiently collect assessment data and modify an assessment schedule based on the analyses. The methods and systems can control the timing of each assessment in order to collect data at times and under conditions that are most informative about the physical subject. Such adaptive methods and systems significantly minimize the frequency of data collection without loss in accuracy or precision and can increase test reliability through reduction in redundancy. The ability to estimate an unknown, underlying function using a small number of free parameters that remain constant regardless of the number of data points being estimated substantially reduces the error of the function estimate. Because estimates of the measurement error are achieved with a minimum of sampled assessments, and with great accuracy, the statistical power of clinical trials, for example, can be greatly increased.Type: GrantFiled: June 16, 2016Date of Patent: February 28, 2023Assignees: NORTHEASTERN UNIVERSITY, THE SCHEPENS EYE RESEARCH INSTITUTE, INC.Inventors: Peter John Bex, John F. Ackermann, Tobias Elze
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Publication number: 20180190380Abstract: Methods and systems providing adaptive assessment of a physical subject to efficiently collect assessment data and modify an assessment schedule based on the analyses. The methods and systems can control the timing of each assessment in order to collect data at times and under conditions that are most informative about the physical subject. Such adaptive methods and systems significantly minimize the frequency of data collection without loss in accuracy or precision and can increase test reliability through reduction in redundancy. The ability to estimate an unknown, underlying function using a small number of free parameters that remain constant regardless of the number of data points being estimated substantially reduces the error of the function estimate. Because estimates of the measurement error are achieved with a minimum of sampled assessments, and with great accuracy, the statistical power of clinical trials, for example, can be greatly increased.Type: ApplicationFiled: June 16, 2016Publication date: July 5, 2018Inventors: Peter John Bex, John F. Ackermann, Tobias Elze
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Patent number: 7003959Abstract: A high temperature splash plate for use in the combustor of a gas turbine engine that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the surface of the splash plate of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector then is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The surface reflects radiation in the direction of the turbine back into the hot gas flow path. The reflected radiation is not focused onto any other hardware component.Type: GrantFiled: December 31, 2002Date of Patent: February 28, 2006Assignee: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Bangalore A. Nagaraj, Craig D. Young, Nicole Justis
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Patent number: 6925811Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the flow path surface of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector then is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a combustor wall. The surface reflects radiation back into the hot gas flow path.Type: GrantFiled: December 31, 2002Date of Patent: August 9, 2005Assignee: General Electric CompanyInventors: Nicole Justis, John F. Ackermann, Paul V. Arszman, Bangalore A. Nagaraj, Craig D. Young
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Patent number: 6926496Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path.Type: GrantFiled: December 31, 2002Date of Patent: August 9, 2005Assignee: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Bangalore A. Nagaraj
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Patent number: 6893737Abstract: A low cost aluminide process for moderate temperature applications. A gas turbine engine component is cleaned and coated with a layer of metal, generally aluminum, containing paint. The metal containing paint layer is heated to a first temperature for a first period of time in an air environment to volatilize the solvents in the paint. The metal containing paint layer is heated to a second temperature for a second period of time in an oxygen-free atmosphere to volatilize the solvents in the paint. The now metal layer and component are heated to a third temperature for a third period of time to interdiffuse the metal and the metal of the component. The component and diffusion layer are then cooled to ambient temperature.Type: GrantFiled: December 27, 2002Date of Patent: May 17, 2005Assignee: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Andrew J. Skoog
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Patent number: 6884524Abstract: A low cost chromide and chromide/aluminide process for moderate temperature applications. A gas turbine engine component is cleaned and coated with a layer of metal, generally chromium or chromium and aluminum, containing paint. The metal containing paint layer is heated to a first temperature for a first period of time in an air environment to volatilize the solvents in the paint. The metal containing paint layer is heated to a second temperature for a second period of time in an oxygen-free atmosphere to volatilize the solvents in the paint. The now metal layer and component are heated to a third temperature for a third period of time to interdiffuse the metal and the metal of the component. The component and diffusion layer are then cooled to ambient temperature.Type: GrantFiled: December 27, 2002Date of Patent: April 26, 2005Assignee: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Andrew J. Skoog
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Publication number: 20040185295Abstract: A low cost aluminide process for moderate temperature applications. A gas turbine engine component is cleaned and coated with a layer of metal, generally aluminum, containing paint. The metal containing paint layer is heated to a first temperature for a first period of time in an air environment to volatilize the solvents in the paint. The metal containing paint layer is heated to a second temperature for a second period of time in an oxygen-free atmosphere to volatilize the solvents in the paint. The now metal layer and component are heated to a third temperature for a third period of time to interdiffuse the metal and the metal of the component. The component and diffusion layer are then cooled to ambient temperature.Type: ApplicationFiled: December 27, 2002Publication date: September 23, 2004Applicant: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Andrew J. Skoog
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Publication number: 20040123598Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the flow path surface of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector then is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a combustor wall. The surface reflects radiation back into the hot gas flow path.Type: ApplicationFiled: December 31, 2002Publication date: July 1, 2004Applicant: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Bangalore A. Nagaraj, Craig D. Young, Nicole Justis
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Publication number: 20040126496Abstract: A low cost chromide and chromide/aluminide process for moderate temperature applications. A gas turbine engine component is cleaned and coated with a layer of metal, generally chromium or chromium and aluminum, containing paint. The metal containing paint layer is heated to a first temperature for a first period of time in an air environment to volatilize the solvents in the paint. The metal containing paint layer is heated to a second temperature for a second period of time in an oxygen-free atmosphere to volatilize the solvents in the paint. The now metal layer and component are heated to a third temperature for a third period of time to interdiffuse the metal and the metal of the component. The component and diffusion layer are then cooled to ambient temperature.Type: ApplicationFiled: December 27, 2002Publication date: July 1, 2004Applicant: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Andrew J. Skoog
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Publication number: 20040126229Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a turbine nozzle. The surface reflects radiation back into the hot gas flow path.Type: ApplicationFiled: December 31, 2002Publication date: July 1, 2004Applicant: General Electric CompanyInventors: John F. Ackermann, Paul V. Arszman, Bangalore A. Nagaraj
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Publication number: 20040123599Abstract: A high temperature gas turbine component for use in the gas flow path that also is a specular optical reflector. A thin layer of a high temperature reflector is applied to the gas flow path of the component, that is, the surface of the component that forms a boundary for hot combustion gases. The component typically includes a thermal barrier coating overlying the high temperature metallic component that permits the component to operate at elevated temperatures. The thermal barrier coating must be polished in order to provide a surface that can suitably reflect the radiation into the gas flow path. A thin layer of the high temperature reflector the is applied over the polished thermal barrier coating by a process that can adequately adhere the reflector to the polished surface without increasing the roughness of the surface. The high temperature reflector can be applied to any surface aft of the compressor, such as on a centerbody.Type: ApplicationFiled: December 31, 2002Publication date: July 1, 2004Inventors: John F. Ackermann, Paul V. Arszman, Bangalore A. Nagaraj, Craig Young, Nicole Justis