Patents by Inventor Lois J. Weir
Lois J. Weir 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: 7895820Abstract: A system of controlling airflow into a pulse detonation engine includes a rotary airflow controller valve receiving air from a high-speed inlet. An engine frame includes a plurality of detonation chambers. A sealing mechanism is between the rotary airflow controller valve and the engine frame. The sealing mechanism is associated with the engine frame and limits leakage of a gas from a first of the detonation chambers to a second of the detonation chambers.Type: GrantFiled: November 16, 2006Date of Patent: March 1, 2011Assignee: Techland Research, Inc.Inventors: Bobby W. Sanders, Charlotte A. Sanders, Lois J. Weir
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Publication number: 20110000548Abstract: A supersonic inlet includes a cowl and an innerbody. An airflow duct entrance, between the cowl and the centerbody, receives an incoming airflow. An airflow duct exit, between the cowl and the centerbody, delivers a subsonic airflow. A controlled airflow separation initiator, on the innerbody and upstream of a lip of the cowl, which, when actuated, creates a separation in the incoming airflow. The separation region changes the local flow field aerodynamics such that an airflow weight flow at the cowl lip matches an airflow weight flow at a duct minimum area, between the airflow duct entrance and the airflow duct exit.Type: ApplicationFiled: February 22, 2010Publication date: January 6, 2011Inventors: Bobby W. Sanders, Charlotte A. Sanders, Lois J. Weir
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Publication number: 20090120059Abstract: A system of controlling airflow into a pulse detonation engine includes a rotary airflow controller valve receiving air from a high-speed inlet. An engine frame includes a plurality of detonation chambers. A sealing mechanism is between the rotary airflow controller valve and the engine frame. The sealing mechanism is associated with the engine frame and limits leakage of a gas from a first of the detonation chambers to a second of the detonation chambers.Type: ApplicationFiled: November 16, 2006Publication date: May 14, 2009Inventors: Bobby W. Sanders, Charlotte A. Sanders, Lois J. Weir
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Patent number: 7048229Abstract: All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall sonic boom signature of the aircraft. These inlets have very high internal area contraction or compression and very low external surface angles. All shocks from the internal inlet surfaces are captured and reflected inside the inlet duct, and all of the external nacelle surfaces are substantially aligned with the external airflow. The inlet shock stability system consists of bleed regions that duct bleed airflows to variable area exits with passive or active exit area controls. This reduces the risk of inlet unstarts by removing airflow through a large open throat bleed region to compensate for reductions in diffuser (engine) corrected airflow demand.Type: GrantFiled: September 26, 2001Date of Patent: May 23, 2006Assignee: Techland Research, Inc.Inventors: Bobby W. Sanders, Lois J. Weir
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Patent number: 6920890Abstract: The invention provides an airflow controller for a propulsion inlet system including a bleed section having two or more bleed plenum chambers, each of the chambers having a porous inlet surface and an exit surface and two or more plates slidably mounted to the bleed section and in fluid communication with the exit surface of the bleed section; and two or more plates being adjustable in multiple positions with respect to the exit surface of the bleed plenum chambers.Type: GrantFiled: July 30, 2002Date of Patent: July 26, 2005Assignee: Techland Research, Inc.Inventors: Bobby W. Sanders, Charlotte A. Sanders, Lois J. Weir
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Patent number: 6705569Abstract: A mixed compression supersonic inlet system is provided which includes an external cowl, and an axisymmetric centerbody which preferably translates fore and aft. The centerbody of the inlet system is further provided with indexing segments which circumferentially rotate to provide longitudinal grooves or channels located on the outer periphery of the centerbody and which increase the effective flow area of the inlet. As the indexing segments rotate circumferentially, the channel width varies. The centerbody may also be provided with indexing segments formed of a first and second portion having hinged joints which slide forward and aft in a groove. One end of the indexing segment is hinged to the non-translating section of a translating centerbody. The indexing segments are positioned over a longitudinal channel. As the translating centerbody is translated forward, the hinges of the indexing segment slide in their respective grooves to expose the channel.Type: GrantFiled: May 9, 2001Date of Patent: March 16, 2004Inventors: Bobby W. Sanders, Lois J. Weir
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Patent number: 6637187Abstract: A rotary inlet flow controller, with one or more open ducts extending therethrough, aerodynamically controls the amount and velocity of the flow of air to combustion chambers of pulse detonation engines, or other engines, without imposing large cyclic airflow transients in the diffuser of the air intake. The ducted rotary inlet flow controller supplies airflow and sealing in synchronization with the cycles of the engine: airflow and fueling supply, sealing, combustion, and re-opening for additional airflow. This controller will supply near-uniform, continuous airflow to the engine. The preferred controller has one or more propeller-like blades that are designed to cyclically and sequentially duct incoming flow to the inlet ports of the combustion chambers, while also providing the capability of sealing the ports during combustion.Type: GrantFiled: September 7, 2001Date of Patent: October 28, 2003Assignee: TechLand Research, Inc.Inventors: Bobby W. Sanders, Lois J. Weir
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Publication number: 20030154707Abstract: A rotary inlet flow controller, with one or more open ducts extending therethrough, aerodynamically controls the amount and velocity of the flow of air to combustion chambers of pulse detonation engines, or other engines, without imposing large cyclic airflow transients in the diffuser of the air intake. The ducted rotary inlet flow controller supplies airflow and sealing in synchronization with the cycles of the engine: airflow and fueling supply, sealing, combustion, and re-opening for additional airflow. This controller will supply near-uniform, continuous airflow to the engine. The preferred controller has one or more propeller-like blades that are designed to cyclically and sequentially duct incoming flow to the inlet ports of the combustion chambers, while also providing the capability of sealing the ports during combustion.Type: ApplicationFiled: September 7, 2001Publication date: August 21, 2003Inventors: Bobby W. Sanders, Lois J. Weir
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Publication number: 20030034066Abstract: The invention provides an airflow controller for a propulsion inlet system including a bleed section having two or more bleed plenum chambers, each of the chambers having a porous inlet surface and an exit surface and two or more plates slidably mounted to the bleed section and in fluid communication with the exit surface of the bleed section; and two or more plates being adjustable in multiple positions with respect to the exit surface of the bleed plenum chambers.Type: ApplicationFiled: July 30, 2002Publication date: February 20, 2003Inventors: Bobby W. Sanders, Charlotte A. Sanders, Lois J. Weir
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Publication number: 20020117581Abstract: All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall sonic boom signature of the aircraft. These inlets have very high internal area contraction or compression and very low external surface angles. All shocks from the internal inlet surfaces are captured and reflected inside the inlet duct, and all of the external nacelle surfaces are substantially aligned with the external airflow. The inlet shock stability system consists of bleed regions that duct bleed airflows to variable area exits with passive or active exit area controls. This reduces the risk of inlet unstarts by removing airflow through a large open throat bleed region to compensate for reductions in diffuser (engine) corrected airflow demand.Type: ApplicationFiled: February 12, 2002Publication date: August 29, 2002Inventors: Bobby W. Sanders, Lois J. Weir
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Patent number: 6276632Abstract: A mixed compression supersonic inlet system is provided which includes an external cowl, and an axisymmetric centerbody which preferably translates fore and aft. The centerbody of the inlet system is further provided with indexing segments which circumferentially rotate to provide longitudinal grooves or channels located on the outer periphery of the centerbody and which increase the effective flow area of the inlet. As the indexing segments rotate circumferentially, the channel width varies. The centerbody may also be provided with indexing segments formed of a first and second portion having hinged joints which slide forward and aft in a groove. One end of the indexing segment is hinged to the non-translating section of a translating centerbody. The indexing segments are positioned over a longitudinal channel. As the translating centerbody is translated forward, the hinges of the indexing segment slide in their respective grooves to expose the channel.Type: GrantFiled: September 16, 1999Date of Patent: August 21, 2001Inventors: Bobby W. Sanders, Lois J. Weir