Patents by Inventor Thomas Kupiszewski
Thomas Kupiszewski 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: 10415897Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.Type: GrantFiled: November 17, 2014Date of Patent: September 17, 2019Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Mehdi Milani Baladi, John Andrew Kemme, Christopher Charles Glynn, Steven Douglas Johnson, Michael Jay Epstein
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Patent number: 10378835Abstract: A heat exchanger includes a cooling air conduit having multiple baffles, a hot air conduit having multiple passes through the cooling air conduit and forming multiple intersections with the baffles, and multiple perforations extending through the baffles. A cooling air flow passes through the baffles, rather than strictly between the baffles, and improves heat-transfer characteristics of the heat exchanger.Type: GrantFiled: March 25, 2016Date of Patent: August 13, 2019Assignee: Unison Industries, LLCInventors: Michael Thomas Kenworthy, William Dwight Gerstler, Daniel Jason Erno, Thomas Kupiszewski, Joseph Robert Coleman
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Publication number: 20190217963Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.Type: ApplicationFiled: March 27, 2019Publication date: July 18, 2019Inventors: Thomas Kupiszewski, Brandon Wayne Miller, Daniel Alan Niergarth, Randy M. Vondrell
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Patent number: 10344674Abstract: A transduct segment, that can include a main tube extending from a first end to a second end and defining a hollow passageway therethrough, a lower platform attached to an outer surface of the main tube on first side of an aperture defined within the main tube, and an upper platform attached to the outer surface of the main tube on second side of the aperture that is opposite of the first side, is provided. The upper platform is integral with the lower platform to define a supply channel therebetween, and the supply channel is in fluid communication with the hollow passageway of the main tube through the aperture defined by the main tube. The lower platform and the upper platform define an interface defining a plurality of channels in fluid communication with the hollow passageway defined by the main tube.Type: GrantFiled: January 8, 2016Date of Patent: July 9, 2019Assignee: General Electric CompanyInventors: Matthew Robert Cerny, Jeffrey Raymond Menard, Thomas Kupiszewski, Johnathen Pegram
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Patent number: 10308366Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.Type: GrantFiled: August 22, 2016Date of Patent: June 4, 2019Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Brandon Wayne Miller, Daniel Alan Niergarth, Randy M. Vondrell
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Patent number: 10209009Abstract: A heat exchanger includes a core defining a first passageway and a second passageway. The core includes a plurality of unit cells coupled together. Each unit cell of the plurality of unit cells includes a first wall and a second wall. The second wall is spaced from the first wall. The first wall at least partially defines a first passageway portion and a second passageway portion. The second wall at least partially defines the second passageway portion. The second wall extends about the first wall such that the first passageway portion is nested within the second passageway portion.Type: GrantFiled: January 3, 2017Date of Patent: February 19, 2019Assignee: General Electric CompanyInventors: William Dwight Gerstler, Thomas Kupiszewski, Michael Thomas Kenworthy, Daniel Jason Erno
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Patent number: 10184400Abstract: Methods of cooling a hot fluid in an annular duct of a gas turbine engine are provided. The method can include directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, and passing a cooling fluid through the annular duct such that the cooling fluid passes between the radially layered cooling channels. Additionally or alternatively, the method can include passing the hot fluid into a first inner radial tube, through a plurality of cooling channels defined within a plurality of curvilinear plates that are radially layered within the annular duct, and into a second inner radial tube; and passing a cooling fluid through the annular duct.Type: GrantFiled: January 8, 2016Date of Patent: January 22, 2019Assignee: General Electric CompanyInventors: Matthew Robert Cerny, Jeffrey Raymond Menard, Thomas Kupiszewski, Johnathen Pegram
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Patent number: 10126062Abstract: An annular heat exchanger for a gas turbine engine is provided. The annular heat exchanger can include a first annular ring comprising a first main tube defined by a plurality of transduct segments; a second annular ring comprising a second main tube defined by a plurality of transduct segments and a curvilinear plate defining at least one channel therein that is in fluid communication with a transduct segment of the first main tube and a transduct segment of the second main tube.Type: GrantFiled: January 8, 2016Date of Patent: November 13, 2018Assignee: General Electric CompanyInventors: Matthew Robert Cerny, Jeffrey Raymond Menard, Thomas Kupiszewski, Johnathen Pegram
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Patent number: 10093428Abstract: A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.Type: GrantFiled: August 22, 2016Date of Patent: October 9, 2018Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Brandon Wayne Miller, Randy M. Vondrell
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Patent number: 10071811Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.Type: GrantFiled: August 22, 2016Date of Patent: September 11, 2018Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Brandon Wayne Miller, Randy M. Vondrell, Paul Robert Gemin
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Patent number: 10006369Abstract: A method and system for a heat exchanger are provided. The heat exchanger includes a plurality of arcuate heat exchanger segments, each including a first header configured to extend circumferentially about at least a portion of a circumference of an internal surface of a fluid duct. The heat exchanger also includes a second header configured to extend circumferentially about the portion spaced axially apart from the first header in a direction opposite of fluid flow through the fluid duct and a first plurality of heat exchanger tubes extending generally axially between the first header and the second header, the first plurality of heat exchanger tubes each including a first flow path separate from a second flow path of any other of the first plurality of heat exchanger tubes, the first flow path changing direction along the flow path from the first header to the second header.Type: GrantFiled: June 18, 2015Date of Patent: June 26, 2018Assignee: General Electric CompanyInventor: Thomas Kupiszewski
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Publication number: 20180050807Abstract: A propulsion system includes an electric propulsor and a gas turbine engine. The propulsion system also includes an electric machine coupled to a rotary component of the gas turbine engine generating a voltage at a baseline voltage magnitude during operation of the gas turbine engine. An electric communication bus is provided electrically connecting the electric machine to the electric propulsor. The propulsion system additionally includes a means for providing a differential voltage to the electric propulsor equal to about twice the baseline voltage magnitude.Type: ApplicationFiled: August 22, 2016Publication date: February 22, 2018Inventors: Thomas Kupiszewski, Brandon Wayne Miller, Randy M. Vondrell
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Publication number: 20180051702Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. An electric communication bus is electrically connected to the electric machine and extends through the core air flowpath to, e.g., electrically connect the electric machine to one or more systems of the gas turbine engine or a propulsion system including the gas turbine engine.Type: ApplicationFiled: August 22, 2016Publication date: February 22, 2018Inventors: Thomas Kupiszewski, Brandon Wayne Miller, Randy M. Vondrell, Paul Robert Gemin
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Publication number: 20180050806Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the turbine section. An electric machine is mounted coaxially with the rotary component and positioned at least partially inward of the core air flowpath along a radial direction of the gas turbine engine. A cavity wall defines at least in part a buffer cavity surrounding at least a portion of the electric machine to thermally insulate the electric machine, e.g., from the relatively high temperatures within the core air flowpath.Type: ApplicationFiled: August 22, 2016Publication date: February 22, 2018Inventors: Thomas Kupiszewski, Brandon Wayne Miller, Daniel Alan Niergarth, Randy M. Vondrell
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Publication number: 20180051701Abstract: A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. The rotary component is rotatable with the compressor section and the turbine section. The gas turbine engine additionally includes an electric machine rotatable with the rotary component and positioned coaxially with the rotary component at least partially inward of the core air flowpath. The electric machine is flexibly mounted to a static frame member, or flexibly coupled to the rotary component, or both, such that the electric machine is mechanically isolated or insulated from various internal and external forces on the gas turbine engine.Type: ApplicationFiled: August 22, 2016Publication date: February 22, 2018Inventors: Thomas Kupiszewski, Brandon Wayne Miller, Daniel Alan Niergarth, Randy M. Vondrell, Paul Robert Gemin
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Publication number: 20170367218Abstract: A heat exchanger includes a core defining a first passageway and a second passageway. The core includes a plurality of unit cells coupled together. Each unit cell of the plurality of unit cells includes a first wall and a second wall. The second wall is spaced from the first wall. The first wall at least partially defines a first passageway portion and a second passageway portion. The second wall at least partially defines the second passageway portion. The second wall extends about the first wall such that the first passageway portion is nested within the second passageway portion.Type: ApplicationFiled: January 3, 2017Publication date: December 21, 2017Inventors: William Dwight Gerstler, Thomas Kupiszewski, Michael Thomas Kenworthy, Daniel Jason Erno
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Patent number: 9835380Abstract: A heat exchanger that includes an input cavity defined by inlet cavity walls; a heat exchanger portion in fluid communication with the input cavity and defined between a first side and a second side, and wherein a plurality of baffles are positioned within the heat exchanger portion; and an outlet cavity in fluid communication with the heat exchanger portion and defined by outlet cavity walls. The heat exchanger portion comprises: a plurality of first fluid paths defined between the baffles and extending from the input cavity to the outlet cavity, and a plurality of tubes extending through the heat exchanger portion from the first side to the second side. Each tube extends through the baffles so as to define a second fluid path through the heat exchanger portion. Heat exchanger systems are also generally provided, along with methods for cooling a hot fluid input with a heat exchanger.Type: GrantFiled: March 13, 2015Date of Patent: December 5, 2017Assignee: General Electric CompanyInventors: Thomas Kupiszewski, Jeffrey Douglas Rambo, James F. Bonar, Jared Wolfe
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Publication number: 20170276440Abstract: A heat exchanger includes a cooling air conduit having multiple baffles, a hot air conduit having multiple passes through the cooling air conduit and forming multiple intersections with the baffles, and multiple perforations extending through the baffles. A cooling air flow passes through the baffles, rather than strictly between the baffles, and improves heat-transfer characteristics of the heat exchanger.Type: ApplicationFiled: March 25, 2016Publication date: September 28, 2017Inventors: Michael Thomas Kenworthy, William Dwight Gerstler, Daniel Jason Erno, Thomas Kupiszewski, Joseph Robert Coleman
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Publication number: 20170205145Abstract: A heat exchanger is provided having an integrally and seamlessly formed return manifold connecting multiple supply tubes and return tubes. The heat exchanger may also include a return manifold having one or more structures providing a flow restriction within or proximate the return manifold.Type: ApplicationFiled: January 20, 2016Publication date: July 20, 2017Inventors: John Alan Manteiga, Michael Thomas Kenworthy, Jared Matthew Wolfe, Thomas Kupiszewski, Jeffrey Douglas Rambo, James Fitzgerald Bonar
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Publication number: 20170198638Abstract: Methods of cooling a hot fluid in an annular duct of a gas turbine engine are provided. The method can include directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, and passing a cooling fluid through the annular duct such that the cooling fluid passes between the radially layered cooling channels. Additionally or alternatively, the method can include passing the hot fluid into a first inner radial tube, through a plurality of cooling channels defined within a plurality of curvilinear plates that are radially layered within the annular duct, and into a second inner radial tube; and passing a cooling fluid through the annular duct.Type: ApplicationFiled: January 8, 2016Publication date: July 13, 2017Inventors: Matthew Robert Cerny, Jeffrey Raymond Menard, Thomas Kupiszewski, Johnathen Pegram