Patents by Inventor Neal D. Domel
Neal D. Domel 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: 10054048Abstract: An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.Type: GrantFiled: July 26, 2013Date of Patent: August 21, 2018Assignee: Lockheed Martin CorporationInventors: Dan J. Baruzzini, Daniel N. Miller, Neal D. Domel, Jeff G. Hakes
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Patent number: 9995181Abstract: An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.Type: GrantFiled: November 30, 2011Date of Patent: June 12, 2018Assignee: Lockheed Martin CorporationInventors: Daniel N. Miller, Neal D. Domel, Dan J. Baruzzini
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Patent number: 9896192Abstract: An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil.Type: GrantFiled: December 13, 2011Date of Patent: February 20, 2018Assignee: Lockheed Martin CorrorationInventors: Neal D. Domel, Eric F. Charlton, Daniel N. Miller
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Patent number: 9551297Abstract: Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.Type: GrantFiled: December 4, 2015Date of Patent: January 24, 2017Assignee: Lockheed Martin CorporationInventors: Neal D. Domel, Daniel N. Miller
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Publication number: 20160084199Abstract: Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.Type: ApplicationFiled: December 4, 2015Publication date: March 24, 2016Inventors: Neal D. Domel, Daniel N. Miller
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Patent number: 9261047Abstract: Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.Type: GrantFiled: May 29, 2012Date of Patent: February 16, 2016Assignee: Lockheed Martin CorporationInventors: Neal D. Domel, Daniel N. Miller
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Publication number: 20150027545Abstract: An apparatus for suppressing shock-induced separation of high speed airflow from a relatively low-energy boundary layer. The apparatus may include an actuator or array of actuators configured to alternately inhale and exhale fluid and positioned to alternately inhale fluid from and exhale fluid into a boundary layer of a fluid mass flowing along the wall. The actuator may be positioned to inhale fluid from a boundary layer separation bubble induced by a supersonic shock wave propagated in the fluid mass.Type: ApplicationFiled: July 26, 2013Publication date: January 29, 2015Applicant: Lockheed Martin CorporationInventors: Dan J. Baruzzini, Daniel N. Miller, Neal D. Domel, Jeff G. Hakes
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Publication number: 20130318944Abstract: Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.Type: ApplicationFiled: May 29, 2012Publication date: December 5, 2013Applicant: Lockheed Martin CorporationInventors: Neal D. Domel, Daniel N. Miller
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Publication number: 20130146715Abstract: An airfoil tip vortex mitigation arrangement comprising one or more flow directors configured and positioned to re-direct freestream air over a low pressure surface of an airfoil in such a way as to displace and weaken a main tip vortex generated at a tip of the airfoil.Type: ApplicationFiled: December 13, 2011Publication date: June 13, 2013Applicant: Lockheed Martin CorrorationInventors: Neal D. Domel, Eric F. Charlton, Daniel N. Miller
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Publication number: 20130133857Abstract: An exhaust impingement cooling device for reducing heating effects of an exhaust plume on an impinged surface. An exhaust nozzle exit screen is positioned across an exhaust plume flow path, and includes a plurality of flowpath diverging apertures that spread at least a portion of an exhaust plume that is being emitted along the exhaust plume flow path from an exhaust plume source. Flow control jets are arrayed within the exhaust plume flow path in respective positions where their operation will augment the flow of exhaust plume gases through the screen, thereby increasing the momentum and mixing of the exhaust plume with cooler ambient air.Type: ApplicationFiled: November 30, 2011Publication date: May 30, 2013Applicant: Lockheed Martin CorporationInventors: Daniel N. Miller, Neal D. Domel, Dan J. Baruzzini
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Patent number: 8403271Abstract: A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.Type: GrantFiled: August 24, 2010Date of Patent: March 26, 2013Assignee: Lockheed Martin CorporationInventors: Neal D. Domel, Dan J. Baruzzini, Daniel N. Miller
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Patent number: 8316631Abstract: An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be occupied by an exhaust plume when the engine is running. A flow generator transmits fluid flow into such an exhaust plume through the injectors. Each injector emits fluid in at least two divergent directions to increase the cross-sectional area of the exhaust plume by forming fluidic lobes in the exhaust plume.Type: GrantFiled: September 30, 2010Date of Patent: November 27, 2012Assignee: Lockheed Martin CorporationInventors: Daniel N. Miller, Neal D. Domel, Cole W. Schemm
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Publication number: 20120079803Abstract: An apparatus for reducing heating effects of an exhaust plume of a jet engine on an impinged surface includes fluid injectors disposed adjacent and aimed into an exhaust plume zone that's to be occupied by an exhaust plume when the engine is running. A flow generator transmits fluid flow into such an exhaust plume through the injectors. Each injector emits fluid in at least two divergent directions to increase the cross-sectional area of the exhaust plume by forming fluidic lobes in the exhaust plume.Type: ApplicationFiled: September 30, 2010Publication date: April 5, 2012Applicant: Lockheed Martin CorporationInventors: Daniel N. Miller, Neal D. Domel, Cole W. Schemm
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Publication number: 20120049008Abstract: A tapered micro-plow, or a series of tapered micro-plows, are submerged in a boundary layer just upstream of a reflection point of an oblique shock. Each micro-plow develops a beneficial pair of vortices which redistribute high energy flow within the boundary layer such that flow separation is prevented or delayed. The beneficial vortex pairs rotate about an axis that is parallel to the flow of fluid, and together rotate such that they induce a velocity on one another which tends to hold them near the surface and delay vortex lift-off.Type: ApplicationFiled: August 24, 2010Publication date: March 1, 2012Applicant: LOCKHEED MARTIN CORPORATIONInventors: Neal D. Domel, Dan J. Baruzzini, Daniel N. Miller
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Publication number: 20110293421Abstract: A rotor blade includes a bleed path opening to a suction surface, extending through the blade, exiting to at least one of the suction or a trailing surface, and through which working fluid flows under centrifugal pumping forces when the blade rotates, to passively bleed working fluid from the suction surface.Type: ApplicationFiled: May 28, 2010Publication date: December 1, 2011Applicant: Lockheed Martin CorporationInventors: Brett W. Denner, Neal D. Domel