Patents by Inventor Thomas A. Kaemming
Thomas A. Kaemming 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: 8210474Abstract: An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on.Type: GrantFiled: October 28, 2008Date of Patent: July 3, 2012Assignee: The Boeing CompanyInventors: Richard S. Dyer, Thomas A. Kaemming, Samuel E. Horne, III
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Patent number: 7721989Abstract: An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on.Type: GrantFiled: March 1, 2006Date of Patent: May 25, 2010Assignee: The Boeing CompanyInventors: Richard S Dyer, Thomas A Kaemming, Samuel E Horne, III
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Publication number: 20100025542Abstract: An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on.Type: ApplicationFiled: October 28, 2008Publication date: February 4, 2010Applicant: The Boring CompanyInventors: Richard S. Dyer, Thomas A. Kaemming, Samuel E. Horne, III
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Publication number: 20090114774Abstract: An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on.Type: ApplicationFiled: March 1, 2006Publication date: May 7, 2009Inventors: Richard S. Dyer, Thomas A. Kaemming, Samuel E. Horne, III
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Patent number: 6494034Abstract: A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber.Type: GrantFiled: November 13, 2001Date of Patent: December 17, 2002Assignee: McDonnell Douglas CorporationInventors: Thomas A. Kaemming, Paul G. Willhite
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Patent number: 6446428Abstract: A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber.Type: GrantFiled: November 13, 2001Date of Patent: September 10, 2002Assignee: McDonnell Douglas CorporationInventors: Thomas A. Kaemming, Paul G. Willhite, Richard S. Dyer, Michael A. Guntorius
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Publication number: 20020078679Abstract: A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber.Type: ApplicationFiled: November 13, 2001Publication date: June 27, 2002Applicant: McDonnell Douglas CorporationInventors: Thomas A. Kaemming, Paul G. Willhite, Richard S. Dyer, Michael A. Guntorius
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Publication number: 20020059793Abstract: A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber.Type: ApplicationFiled: November 13, 2001Publication date: May 23, 2002Inventors: Thomas A. Kaemming, Paul G. Willhite, Richard S. Dyer, Michael A. Guntorius
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Patent number: 6347509Abstract: A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber. The pulsed detonation engine includes a volume of ejector/bypass air surrounding the detonation chamber, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet end.Type: GrantFiled: July 15, 1999Date of Patent: February 19, 2002Assignee: McDonnell Douglas Corporation c/o The Boeing CompanyInventors: Thomas A. Kaemming, Paul G. Willhite, Richard S. Dyer, Michael A. Guntorius