Patents by Inventor Michael F. Stoia
Michael F. Stoia 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: 11927402Abstract: Systems, apparatuses, and methods relating to heat transfer devices having nested layers of helical fluid channels. In some examples, a device for transferring heat includes a set of nested tubular walls and a plurality of helical walls intersecting each of the nested tubular walls to form one or more first channel layers nested with one or more second channel layers. Each of the first and second channel layers includes a plurality of helical fluid channels. A first intake and a first outtake are in fluid communication with one another via the plurality of helical fluid channels of each first channel layer, for flow of a first fluid through the device. A second intake and a second outtake are in fluid communication with one another via the plurality of helical fluid channels of each second channel layer, for flow of a second fluid through the device.Type: GrantFiled: July 13, 2021Date of Patent: March 12, 2024Assignee: The Boeing CompanyInventors: Douglas H. Van Affelen, Arun Muley, Michael F. Stoia
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Patent number: 11747094Abstract: Example heat exchangers and methods of use are described herein. An example heat exchanger includes a lattice structure including a plurality of conduits defining a plurality of interstitial voids between the plurality of conduits. Each of the plurality of conduits includes an inlet and an outlet, and the plurality of conduits are arranged such that, between the inlet and the outlet, each of the conduits intersects at least one other conduit to enable flow between the intersecting conduits. The example heat exchanger also includes a first manifold formed unitarily with the lattice structure, the first manifold comprising a first plurality of openings in fluid communication with each inlet of the plurality of conduits. The example heat exchanger further includes a phase change material (PCM) disposed within and substantially filling the plurality of interstitial voids.Type: GrantFiled: May 12, 2017Date of Patent: September 5, 2023Assignee: The Boeing CompanyInventors: Michael F. Stoia, Arun Muley, Douglas H. Van Afielen
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Publication number: 20230258484Abstract: A material compatibility test design system and method, allowing for the testing of characteristics of behavior of materials in extreme environments, the method including concurrently exposing a test specimen to a first environment and a second environment, the test specimen having an outside surface and an inside surface, the inside surface defining an internal volume, includes exposing the outside surface of the test specimen to the first environment for a predetermined period of time, the first environment comprising a first temperature, a first pressure and a first composition. The method further includes exposing the inside surface of the test specimen to the second environment for a second predetermined period of time, the second environment comprising a second temperature, a second pressure and a second composition.Type: ApplicationFiled: February 16, 2022Publication date: August 17, 2023Applicant: The Boeing CompanyInventors: Bruno Zamorano Senderos, Ali Yousefiani, Austin E. Mann, Michael F. Stoia
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Patent number: 11598285Abstract: Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.Type: GrantFiled: November 23, 2021Date of Patent: March 7, 2023Assignee: The Boeing CompanyInventors: Michael F. Stoia, Garrett W. Ek, Arun Muley, Jacob T. Needels, Kevin G. Bowcutt
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Publication number: 20230015392Abstract: Systems, apparatuses, and methods relating to heat transfer devices having nested layers of helical fluid channels. In some examples, a device for transferring heat includes a set of nested tubular walls and a plurality of helical walls intersecting each of the nested tubular walls to form one or more first channel layers nested with one or more second channel layers. Each of the first and second channel layers includes a plurality of helical fluid channels. A first intake and a first outtake are in fluid communication with one another via the plurality of helical fluid channels of each first channel layer, for flow of a first fluid through the device. A second intake and a second outtake are in fluid communication with one another via the plurality of helical fluid channels of each second channel layer, for flow of a second fluid through the device.Type: ApplicationFiled: July 13, 2021Publication date: January 19, 2023Applicant: The Boeing CompanyInventors: Douglas H. Van Affelen, Arun Muley, Michael F. Stoia
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Patent number: 11465766Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.Type: GrantFiled: June 28, 2019Date of Patent: October 11, 2022Assignee: The Boeing CompanyInventors: Michael F. Stoia, Garrett W. Ek, Arun Muley
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Publication number: 20220260037Abstract: Methods and apparatus for power generation and/or thermal management on a high speed flight vehicle include circulating a power generation loop working fluid through a power generation loop, which absorbs heat associated with the flight vehicle. A generator operably coupled to the power generation loop generates electrical power. Additionally, a heat transport loop working fluid may circulate through a heat transport loop to provide thermal management through heat transfer.Type: ApplicationFiled: November 23, 2021Publication date: August 18, 2022Applicant: The Boeing CompanyInventors: Michael F. Stoia, Joseph S. Silkey, Jacob T. Needels, Kevin G. Bowcutt
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Publication number: 20220260036Abstract: Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.Type: ApplicationFiled: November 23, 2021Publication date: August 18, 2022Applicant: The Boeing CompanyInventors: Michael F. Stoia, Garrett W. Ek, Arun Muley, Jacob T. Needels, Kevin G. Bowcutt
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Patent number: 11378340Abstract: A heat transfer device includes a storage chamber, a coolant housed within the storage chamber, a cooling chamber, one or more heat transfer components, a fluid passage between the storage chamber and the cooling chamber, and a barrier element. The one or more heat transfer components facilitate heat transfer from a heat source outside of the cooling chamber to the cooling chamber. The barrier element may have (i) a closed configuration, and (ii) an open configuration in which the barrier element is configured to allow the coolant in the storage chamber to flow from the storage chamber into the cooling chamber. The barrier element may reconfigure from the closed configuration to the open configuration in response to a trigger condition, such as the coolant housed within the storage chamber reaching a trigger temperature and/or the initial pressure of the coolant housed within the storage chamber reaching a trigger pressure.Type: GrantFiled: June 21, 2018Date of Patent: July 5, 2022Assignee: The Boeing CompanyInventors: Ernest E. Bunch, Christopher C. Veto, James J. Lucas, Garrett W. Ek, Douglas H. Van Affelen, Michael F. Stoia
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Publication number: 20200407072Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.Type: ApplicationFiled: June 28, 2019Publication date: December 31, 2020Applicant: The Boeing CompanyInventors: Michael F. Stoia, Garrett W. Ek, Arun Muley
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Publication number: 20190390911Abstract: A heat transfer device includes a storage chamber, a coolant housed within the storage chamber, a cooling chamber, one or more heat transfer components, a fluid passage between the storage chamber and the cooling chamber, and a barrier element. The one or more heat transfer components facilitate heat transfer from a heat source outside of the cooling chamber to the cooling chamber. The barrier element may have (i) a closed configuration, and (ii) an open configuration in which the barrier element is configured to allow the coolant in the storage chamber to flow from the storage chamber into the cooling chamber. The barrier element may reconfigure from the closed configuration to the open configuration in response to a trigger condition, such as the coolant housed within the storage chamber reaching a trigger temperature; and/or the initial pressure of the coolant housed within the storage chamber reaching a trigger pressure.Type: ApplicationFiled: June 21, 2018Publication date: December 26, 2019Inventors: Ernest E. Bunch, Christopher C. Veto, James J. Lucas, Garrett W. Ek, Douglas H. Van Affelen, Michael F. Stoia
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Patent number: 10480866Abstract: A heat pipe comprises a tube and protrusions. The tube has an internal surface, an external surface, and a length running from a first end to a second end. The protrusions are on the internal surface. A first cross-section of the protrusions at a first location of the length of the tube is different from a second cross-section of the protrusions at a second location of the length of the tube. The tube and the protrusions are monolithic.Type: GrantFiled: January 5, 2017Date of Patent: November 19, 2019Assignee: The Boeing CompanyInventors: Bruce Lee Drolen, Douglas H. Van Affelen, Arun Muley, Michael F. Stoia
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Publication number: 20180328673Abstract: Example heat exchangers and methods of use are described herein. An example heat exchanger includes a lattice structure including a plurality of conduits defining a plurality of interstitial voids between the plurality of conduits. Each of the plurality of conduits includes an inlet and an outlet, and the plurality of conduits are arranged such that, between the inlet and the outlet, each of the conduits intersects at least one other conduit to enable flow between the intersecting conduits. The example heat exchanger also includes a first manifold formed unitarily with the lattice structure, the first manifold comprising a first plurality of openings in fluid communication with each inlet of the plurality of conduits. The example heat exchanger further includes a phase change material (PCM) disposed within and substantially filling the plurality of interstitial voids.Type: ApplicationFiled: May 12, 2017Publication date: November 15, 2018Inventors: Michael F. Stoia, Arun Muley, Douglas H. Van Affelen
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Publication number: 20180187979Abstract: A heat pipe comprises a tube and protrusions. The tube has an internal surface, an external surface, and a length running from a first end to a second end. The protrusions are on the internal surface. A first cross-section of the protrusions at a first location of the length of the tube is different from a second cross-section of the protrusions at a second location of the length of the tube. The tube and the protrusions are monolithic.Type: ApplicationFiled: January 5, 2017Publication date: July 5, 2018Inventors: Bruce Lee Drolen, Douglas H. Van Affelen, Arun Muley, Michael F. Stoia
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Patent number: 9207363Abstract: An anti-reflection nanostructure assembly including an array of nanostructures, wherein each nanostructure of the array includes a proximal end and a distal end, and is tapered from the proximal end to the distal end, and wherein the proximal end of each nanostructure of the array is contiguous with the proximal ends of adjacent nanostructures of the array to form a contiguous layer.Type: GrantFiled: April 30, 2013Date of Patent: December 8, 2015Assignee: The Boeing CompanyInventors: Michael F. Stoia, Authi A. Narayanan, Stephen K. Wilcken
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Patent number: 8957303Abstract: In an embodiment of the disclosure, there is provided a strain isolation layer assembly. The assembly has a rigid solar layer; a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility; and an underlying substrate layer. The strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form a strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.Type: GrantFiled: October 31, 2011Date of Patent: February 17, 2015Assignee: The Boeing CompanyInventors: Robert Erik Grip, Blaine Knight Rawdon, Tab Hunter Crooks, Michael F. Stoia
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Publication number: 20140320967Abstract: An anti-reflection nanostructure assembly including an array of nanostructures, wherein each nanostructure of the array includes a proximal end and a distal end, and is tapered from the proximal end to the distal end, and wherein the proximal end of each nanostructure of the array is contiguous with the proximal ends of adjacent nanostructures of the array to form a contiguous layer.Type: ApplicationFiled: April 30, 2013Publication date: October 30, 2014Applicant: The Boeing CompanyInventors: Michael F. Stoia, Authi A. Narayanan, Stephen K. Wilcken
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Publication number: 20120118345Abstract: Disclosed is an improved thermoelectric component, a method for thermal integration of the improved thermoelectric component in an environment having thermally distinct zones, and a thermoelectric generation system. In general, the thermoelectric component includes a thermoelectric device having opposing surfaces for arrangement in comparatively hot and cold environments, and an extended surface mounted in close proximity to at least one of the opposing surfaces, the extended surface being a layer of porous material having at least a portion immersed in at least one of the hot or cold environments.Type: ApplicationFiled: November 15, 2010Publication date: May 17, 2012Inventors: Michael F. Stoia, David W. Kwok, James P. Huang
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Patent number: 8127758Abstract: An aerospace platform includes a structure having a cavity and a light-transmissive portion that exposes the cavity to sunlight. The aerospace platform further includes a fluid heating system. The fluid heating system includes a fluid-carrying, thermally absorptive structure within the cavity, and a solar collector for collecting light transmitted through the light-transmissive portion and focusing the collected light onto the absorptive structure. The thermally absorptive structure has a high surface absorptivity that retains thermal energy when exposed to solar irradiance and heats fluid contained therein.Type: GrantFiled: March 28, 2008Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventors: Shailesh Atreya, Michael F. Stoia, Tina R. Stoia, Russell K. Jones
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Publication number: 20100192941Abstract: A solar concentration system including at least one receiver and an array of micro-mirrors connected to a substrate, each micro-mirror of the array being articulateable relative to the substrate, wherein the receiver is positioned relative to the array such that the array directs incoming light to the receiver.Type: ApplicationFiled: April 1, 2009Publication date: August 5, 2010Inventors: Michael F. Stoia, David E. Blanding, Matthew R. Sexton