Patents by Inventor Charles P. Gendrich
Charles P. Gendrich 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: 11761337Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.Type: GrantFiled: June 20, 2022Date of Patent: September 19, 2023Assignee: RTX CorporationInventors: Troy Shannon Prince, Matthew E. Bintz, Charles P. Gendrich
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Publication number: 20220316343Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.Type: ApplicationFiled: June 20, 2022Publication date: October 6, 2022Applicant: Raytheon Technologies CorporationInventors: Troy Shannon Prince, Matthew E. Bintz, Charles P. Gendrich
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Patent number: 11391160Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.Type: GrantFiled: June 4, 2019Date of Patent: July 19, 2022Assignee: Raytheon Technologies Inc.Inventors: Troy Shannon Prince, Matthew E. Bintz, Charles P. Gendrich
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Patent number: 11047397Abstract: A gas turbine engine includes a circumferential array of stator vanes that have first and second vanes with different vibrational frequencies than one another. The first vanes are arranged in circumferentially alternating relationship with the second vanes.Type: GrantFiled: December 26, 2014Date of Patent: June 29, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Richard K. Hayford, Robert J. Morris, Charles H. Warner, Charles P. Gendrich
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Patent number: 10801336Abstract: An airfoil has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 3748±15% Hz, a second mode with a frequency of 6416±15% Hz, a third mode with a frequency of 14418±15% Hz, a fourth mode with a frequency of 17417±15% Hz, a fifth mode with a frequency of 19326±15% Hz and a sixth mode with a frequency of 26648±15% Hz.Type: GrantFiled: January 12, 2018Date of Patent: October 13, 2020Assignee: Raytheon Technology CorporationInventors: Charles P. Gendrich, Christopher St. Mary, Xuedong Zhou, Joseph Wieser, Zhen Wu, John Joseph Papalia, Kaliya Balamurugan, Joseph Steele, Jeff M. Carrico, Danoris Garcia-Chabrier
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Publication number: 20200032655Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.Type: ApplicationFiled: June 4, 2019Publication date: January 30, 2020Applicant: United Technologies CorporationInventors: TROY SHANNON PRINCE, Matthew E. Bintz, Charles P. Gendrich
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Patent number: 10352173Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.Type: GrantFiled: March 2, 2016Date of Patent: July 16, 2019Assignee: United Technologies CorporationInventors: Troy Shannon Prince, Matthew E. Bintz, Charles P. Gendrich
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Patent number: 10233841Abstract: In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.Type: GrantFiled: November 5, 2015Date of Patent: March 19, 2019Assignee: United Technologies CorporationInventors: Matthew E. Bintz, Charles P. Gendrich, John C. DiTomasso, Andrew J. Murphy
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Publication number: 20180010459Abstract: The leading edge, the trailing edge, or both may be axially offset for a portion of the airfoils in a disk. By offsetting the airfoils, the downstream wake energy to the next stage of airfoils may be decreased. By staggering airfoils which are offset with airfoils that are not offset, the wake shapes from the airfoils may be out of phase and will not excite the downstream airfoils as much as conventional systems. This may decrease vibration and associated vibratory stresses in the system.Type: ApplicationFiled: January 10, 2017Publication date: January 11, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: CHARLES P. GENDRICH, CHARLES H. ROCHE
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Publication number: 20170254208Abstract: An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.Type: ApplicationFiled: March 2, 2016Publication date: September 7, 2017Applicant: United Technologies CorporationInventors: Troy Shannon Prince, Matthew E. Bintz, Charles P. Gendrich
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Patent number: 9512736Abstract: A method is provided for monitoring one or more rotating turbine engine rotor blades using a processing system and a sensor having a measurement field. The method includes steps of: (i) providing measurement data from the sensor as a first of the rotor blades passes through the measurement field; (ii) correlating the measurement data with reference data as a function of time to provide correlation data; and (iii) processing the correlation data to determine a peak correlation value that corresponds to a point in time during the passage of the first of the rotor blades through the measurement field; wherein the correlating and the processing are performed by the processing system.Type: GrantFiled: May 14, 2012Date of Patent: December 6, 2016Assignee: United Technologies CorporationInventor: Charles P. Gendrich
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Publication number: 20160333894Abstract: A gas turbine engine includes a circumferential array of stator vanes that have first and second vanes with different vibrational frequencies than one another. The first vanes are arranged in circumferentially alternating relationship with the second vanes.Type: ApplicationFiled: December 26, 2014Publication date: November 17, 2016Inventors: Hayford Richard K., Robert J. Morris, Charles H. Warner, Charles P. Gendrich
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Publication number: 20160131036Abstract: In one exemplary embodiment, a gas turbine engine system for cooling engine components includes an engine core, a core housing containing the engine core, an engine core driven fan forward of the core housing, a nacelle surrounding the fan and the core housing, and a bypass duct defined between an outer diameter of the core housing and an inner diameter of the nacelle. Also included is a thermal management system having a coolant circuit including at least one of a first heat exchanger disposed on the inner diameter of the nacelle and a second heat exchanger disposed on a leading edge of a BiFi spanning the bypass duct. The first heat exchanger is in thermal communication with the second heat exchanger.Type: ApplicationFiled: November 5, 2015Publication date: May 12, 2016Inventors: Matthew E. Bintz, Charles P. Gendrich, John C. DiTomasso, Andrew J. Murphy
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Publication number: 20130304418Abstract: A method is provided for monitoring one or more rotating turbine engine rotor blades using a processing system and a sensor having a measurement field. The method includes steps of: (i) providing measurement data from the sensor as a first of the rotor blades passes through the measurement field; (ii) correlating the measurement data with reference data as a function of time to provide correlation data; and (iii) processing the correlation data to determine a peak correlation value that corresponds to a point in time during the passage of the first of the rotor blades through the measurement field; wherein the correlating and the processing are performed by the processing system.Type: ApplicationFiled: May 14, 2012Publication date: November 14, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Charles P. Gendrich
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Publication number: 20130224028Abstract: A component blending tool assembly, includes a material removing surface that is moved to provide a blended area in a component, the material removing surface having a spherical contour mimicking a predetermined depth ratio of the blended area.Type: ApplicationFiled: February 28, 2012Publication date: August 29, 2013Inventors: Nathan D. Korn, Charles P. Gendrich, Jonathan E. Daggett, Robert E. Shepler, David P. Houston, David M. Nissley, Stephen D. Hoyt, Ron I. Prihar
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Patent number: 8465252Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members are tubular in shape and provide a radially extending passage. The anti-vortex members include an outer end having a circumferential side with an opening in fluid communication with the radial passage.Type: GrantFiled: October 13, 2009Date of Patent: June 18, 2013Assignee: United Technologies CorporationInventors: Matthew E. Bintz, Eric W. Malmborg, Charles P. Gendrich
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Publication number: 20130078084Abstract: An air seal assembly for a gas turbine engine the air seal comprises a first assembly and a second assembly. One of the first assembly and the second assembly is rotatable relative to the other of the first assembly and the second assembly. The second assembly is aligned annularly with the first assembly and includes a circumferential surface with an abradable coating disposed annularly adjacent to the first and second airfoil tips. The first assembly includes at least one first airfoil with a first tip having an abrasive coating, and at least one second airfoil with a second tip absent the abrasive coating, the at least one first airfoil co-aligned axially and intermingled with a respective at least one second airfoil around a periphery of the first assembly.Type: ApplicationFiled: September 23, 2011Publication date: March 28, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Charles P. Gendrich, Bradley L. Pike, Christopher R. McNeill, David J. Pitney
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Publication number: 20100266387Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members are tubular in shape and provide a radially extending passage. The anti-vortex members include an outer end having a circumferential side with an opening in fluid communication with the radial passage.Type: ApplicationFiled: October 13, 2009Publication date: October 21, 2010Inventors: Matthew E. Bintz, Eric W. Malmborg, Charles P. Gendrich