Patents by Inventor John T. Schmitz
John T. Schmitz 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: 11684974Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: GrantFiled: June 17, 2022Date of Patent: June 27, 2023Assignee: Raytheon Technologies CorporationInventor: John T. Schmitz
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Publication number: 20220316398Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: ApplicationFiled: June 17, 2022Publication date: October 6, 2022Applicant: Raytheon Technologies CorporationInventor: John T. Schmitz
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Patent number: 11378010Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: GrantFiled: March 26, 2020Date of Patent: July 5, 2022Assignee: Raytheon Technologies CorporationInventor: John T. Schmitz
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Patent number: 11149644Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.Type: GrantFiled: March 21, 2019Date of Patent: October 19, 2021Assignee: Raytheon Technologies CorporationInventors: Frederick M. Schwarz, John T. Schmitz
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Patent number: 10907546Abstract: A heat exchanger system for a gas turbine engine is disclosed. The heat exchanger system may include a first structure at least partially defining a first plenum configured to receive a first air stream, a second structure at least partially defining a second plenum configured to receive a second air stream having lower pressure than the first air stream, a third structure at least partially defining a third plenum configured to receive a third air stream having lower pressure than the second air stream, and a heat exchanger configured for operative communication with the first air stream, the second air stream, and the third air stream while disposed between the second air stream and the third air stream. The heat exchanger may be configured to transfer heat from the first air stream to the third air stream.Type: GrantFiled: May 13, 2019Date of Patent: February 2, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: John T. Schmitz
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Patent number: 10830543Abstract: A heat exchanger system includes an additively manufactured inlet header upstream of, and in fluid communication with, the heat exchanger core and an additively manufactured exit header downstream of, and in fluid communication with, the heat exchanger core. A method of manufacturing a header for a ducted heat exchanger system for a gas turbine engine includes additively manufacturing a header with respect to a desired airflow therethrough.Type: GrantFiled: February 6, 2015Date of Patent: November 10, 2020Assignee: Raytheon Technologies CorporationInventors: John T Schmitz, Neal R Herring, John H Whiton, Joseph Turney, Brian St. Rock, Michael K Ikeda
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Publication number: 20200240328Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: ApplicationFiled: March 26, 2020Publication date: July 30, 2020Applicant: United Technologies CorporationInventor: John T. Schmitz
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Patent number: 10634054Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: GrantFiled: October 19, 2015Date of Patent: April 28, 2020Assignee: United Technologies CorporationInventor: John T Schmitz
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Publication number: 20200025086Abstract: A heat exchanger system for a gas turbine engine is disclosed. The heat exchanger system may include a first structure at least partially defining a first plenum configured to receive a first air stream, a second structure at least partially defining a second plenum configured to receive a second air stream having lower pressure than the first air stream, a third structure at least partially defining a third plenum configured to receive a third air stream having lower pressure than the second air stream, and a heat exchanger configured for operative communication with the first air stream, the second air stream, and the third air stream while disposed between the second air stream and the third air stream. The heat exchanger may be configured to transfer heat from the first air stream to the third air stream.Type: ApplicationFiled: May 13, 2019Publication date: January 23, 2020Inventor: John T. Schmitz
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Patent number: 10450956Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: GrantFiled: October 20, 2015Date of Patent: October 22, 2019Assignee: United Technologies CorporationInventor: John T Schmitz
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Publication number: 20190218973Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.Type: ApplicationFiled: March 21, 2019Publication date: July 18, 2019Inventors: Frederick M. Schwarz, John T. Schmitz
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Patent number: 10287983Abstract: A heat exchanger system for a gas turbine engine is disclosed. The heat exchanger system may include a first structure at least partially defining a first plenum configured to receive a first air stream, a second structure at least partially defining a second plenum configured to receive a second air stream having lower pressure than the first air stream, a third structure at least partially defining a third plenum configured to receive a third air stream having lower pressure than the second air stream, and a heat exchanger configured for operative communication with the first air stream, the second air stream, and the third air stream while disposed between the second air stream and the third air stream. The heat exchanger may be configured to transfer heat from the first air stream to the third air stream.Type: GrantFiled: October 6, 2014Date of Patent: May 14, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: John T. Schmitz
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Patent number: 10240531Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.Type: GrantFiled: January 23, 2017Date of Patent: March 26, 2019Assignee: United Technologies CorporationInventors: Frederick M. Schwarz, John T. Schmitz
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Patent number: 10066496Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least one beam. An anti-vibration seal is disposed in contact with beam and operative to mitigate an externally induced vibratory response of the beam.Type: GrantFiled: January 9, 2015Date of Patent: September 4, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: John T. Schmitz
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Patent number: 9810150Abstract: A heat exchanger assembly for a gas turbine engine including a frame, including a non-planar outer wall, a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween, an inlet side extending between the non-planar outer wall and the non-planar inner wall, an inlet passage extending through the inlet side, an outlet side extending between the non-planar outer wall and the non-planar inner wall opposite the inlet side; an outlet passage extending through the outlet side, and a continuous non-planar core disposed within the frame cavity and in flow communication with the inlet passage and the outlet passage.Type: GrantFiled: August 14, 2015Date of Patent: November 7, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John T. Schmitz, Joe Ott, Lexia Kironn, Evan Butcher
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Publication number: 20170260905Abstract: A heat exchanger system for a gas turbine engine is disclosed. The heat exchanger system may include a first structure at least partially defining a first plenum configured to receive a first air stream, a second structure at least partially defining a second plenum configured to receive a second air stream having lower pressure than the first air stream, a third structure at least partially defining a third plenum configured to receive a third air stream having lower pressure than the second air stream, and a heat exchanger configured for operative communication with the first air stream, the second air stream, and the third air stream while disposed between the second air stream and the third air stream. The heat exchanger may be configured to transfer heat from the first air stream to the third air stream.Type: ApplicationFiled: October 6, 2014Publication date: September 14, 2017Inventor: John T. Schmitz
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Publication number: 20170122210Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.Type: ApplicationFiled: January 23, 2017Publication date: May 4, 2017Inventors: Frederick M. Schwarz, John T. Schmitz
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Publication number: 20160231068Abstract: A heat exchanger system includes an additively manufactured inlet header upstream of, and in fluid communication with, the heat exchanger core and an additively manufactured exit header downstream of, and in fluid communication with, the heat exchanger core. A method of manufacturing a header for a ducted heat exchanger system for a gas turbine engine includes additively manufacturing a header with respect to a desired airflow therethrough.Type: ApplicationFiled: February 6, 2015Publication date: August 11, 2016Inventors: John T. Schmitz, Neal R. Herring, John H. Whiton, Joseph Turney, Brian St. Rock, Michael K. Ikeda
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Publication number: 20160108815Abstract: A heat exchanger assembly for a gas turbine engine including a frame, including a non-planar outer wall, a non-planar inner wall spaced radially inward from the non-planar outer wall to form a frame cavity therebetween, an inlet side extending between the non-planar outer wall and the non-planar inner wall, an inlet passage extending through the inlet side, an outlet side extending between the non-planar outer wall and the non-planar inner wall opposite the inlet side; an outlet passage extending through the outlet side, and a continuous non-planar core disposed within the frame cavity and in flow communication with the inlet passage and the outlet passage.Type: ApplicationFiled: August 14, 2015Publication date: April 21, 2016Inventors: John T. Schmitz, Joe Ott, Lexia Kironn, Evan Butcher
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Publication number: 20160108814Abstract: A ducted heat exchanger system for a gas turbine engine includes an additive manufactured heat exchanger core with a contoured external and/or internal geometry. A method of additively manufacturing a heat exchanger for a gas turbine engine includes additively manufacturing a core of a heat exchanger to set a ratio of local surface area to flow area to control a pressure drop per unit length along the core.Type: ApplicationFiled: October 20, 2015Publication date: April 21, 2016Inventor: John T Schmitz