Patents by Inventor Nate Cooper
Nate Cooper 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: 11105338Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.Type: GrantFiled: September 23, 2019Date of Patent: August 31, 2021Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Michael Nesteroff, Jonathan Acker, Jeffrey Crutchfield, Nate Cooper, Mark Whitlock, Nathan Ottow
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Patent number: 11002284Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.Type: GrantFiled: June 6, 2019Date of Patent: May 11, 2021Assignee: Rolls-Royce CorporationInventors: Michael Nesteroff, Jonathan Acker, Nate Cooper, Nathan Ottow
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Publication number: 20210062824Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.Type: ApplicationFiled: September 23, 2019Publication date: March 4, 2021Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Michael Nesteroff, Jonathan Acker, Jeffrey Crutchfield, Nate Cooper, Mark Whitlock, Nathan Ottow
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Patent number: 10935044Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.Type: GrantFiled: August 1, 2019Date of Patent: March 2, 2021Assignee: Rolls-Royce CorporationInventors: Nathan Ottow, Johnathan Acker, Nate Cooper, Mark Whitlock, Michael Nesteroff
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Publication number: 20190353180Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.Type: ApplicationFiled: August 1, 2019Publication date: November 21, 2019Applicant: Rolls-Royce CorporationInventors: Nathan Ottow, Johnathan Acker, Nate Cooper, Mark Whitlock, Michael Nesteroff
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Patent number: 10458429Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.Type: GrantFiled: August 11, 2016Date of Patent: October 29, 2019Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.Inventors: Michael Nesteroff, Jonathan Acker, Jeffrey Crutchfield, Nate Cooper, Mark Whitlock, Nathan Ottow
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Publication number: 20190323514Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.Type: ApplicationFiled: June 6, 2019Publication date: October 24, 2019Applicant: Rolls-Royce CorporationInventors: Michael Nesteroff, Jonathan Acker, Nate Cooper, Nathan Ottow
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Patent number: 10408226Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.Type: GrantFiled: May 26, 2016Date of Patent: September 10, 2019Assignee: ROLLS-ROYCE CORPORATIONInventors: Nathan Ottow, Jonathan Acker, Nate Cooper, Mark Whitlock, Michael Nesteroff
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Patent number: 10352329Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.Type: GrantFiled: May 26, 2016Date of Patent: July 16, 2019Assignee: ROLLS-ROYCE CORPORATIONInventors: Michael Nesteroff, Jonathan Acker, Nate Cooper, Nathan Ottow
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Patent number: 10309410Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.Type: GrantFiled: May 26, 2016Date of Patent: June 4, 2019Assignee: ROLLS-ROYCE CORPORATIONInventors: Nathan Ottow, Jonathan Acker, Nate Cooper
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Publication number: 20180017078Abstract: An engine includes a compressor having a first compressor, a second compressor, and a static hub transition duct. The first compressor includes a rotatable portion and a static portion. The second compressor is disposed downstream of the first compressor and includes an inlet and a rotatable portion. The static hub transition duct includes an inner wall and an outer wall. The inner wall is secured to the static portion of the first compressor, and the inner wall and outer wall define a space that fluidically couples the first compressor and the inlet of the second compressor.Type: ApplicationFiled: July 12, 2016Publication date: January 18, 2018Inventors: Steven Mazur, Mark Whitlock, Jonathan Acker, Nate Cooper
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Publication number: 20170342994Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.Type: ApplicationFiled: May 26, 2016Publication date: November 30, 2017Applicant: Rolls-Royce CorporationInventors: Michael Nesteroff, Jonathan Acker, Nate Cooper, Nathan Ottow
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Publication number: 20170342996Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.Type: ApplicationFiled: August 11, 2016Publication date: November 30, 2017Applicants: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Michael Nesteroff, Jonathan Acker, Jeffrey Crutchfield, Nate Cooper, Mark Whitlock, Nathan Ottow
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Publication number: 20170343002Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.Type: ApplicationFiled: May 26, 2016Publication date: November 30, 2017Applicant: Rolls-Royce CorporationInventors: Nathan Ottow, Jonathan Acker, Nate Cooper
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Publication number: 20170342995Abstract: A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.Type: ApplicationFiled: May 26, 2016Publication date: November 30, 2017Applicant: Rolls-Royce CorporationInventors: Nathan Ottow, Jonathan Acker, Nate Cooper, Mark Whitlock, Michael Nesteroff