Patents by Inventor Torey Davis
Torey Davis 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: 9685841Abstract: An electrical generating system for an aircraft may include a first shaft connected with an engine gearbox, a second shaft connected with a generator of the aircraft, and a connection unit in which the first and second shafts are selectively engageable with one another. The connection unit may include a solenoid coil, an armature co-axial with the first and the second shafts, a plurality of balls positioned around the armature. The armature may include a first cylindrical segment and a second cylindrical segment. The armature may be selectively movable between a first axial position and a second axial position. When the armature is in a first axial position, the balls are positioned to transmit torque forces between the first shaft and the second shaft. When the armature is in a second axial position, the first shaft and the second shaft are free to rotate independently.Type: GrantFiled: November 12, 2014Date of Patent: June 20, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Torey Davis, Jens Gehrke, Wayne Pearson, Cristian Anghel, Janiece Marie Cooper, Mason Douglas Fritz, Matthew Groff, Tovi F. Johnson, Eric John Watters, Matthew A. Yturralde
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Publication number: 20160134171Abstract: An electrical generating system for an aircraft may include a first shaft connected with an engine gearbox, a second shaft connected with a generator of the aircraft, and a connection unit in which the first and second shafts are selectively engageable with one another. The connection unit may include a solenoid coil, an armature co-axial with the first and the second shafts, a plurality of balls positioned around the armature. The armature may include a first cylindrical segment and a second cylindrical segment. The armature may be selectively movable between a first axial position and a second axial position. When the armature is in a first axial position, the balls are positioned to transmit torque forces between the first shaft and the second shaft. When the armature is in a second axial position, the first shaft and the second shaft are free to rotate independently.Type: ApplicationFiled: November 12, 2014Publication date: May 12, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Torey Davis, Jens Gehrke, Wayne Pearson, Cristian Anghel, Janiece Marie Cooper, Mason Douglas Fritz, Matthew Groff, Tovi F. Johnson, Eric John Watters, Matthew A. Yturralde
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Patent number: 8992161Abstract: Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.Type: GrantFiled: August 26, 2011Date of Patent: March 31, 2015Assignee: Honeywell International Inc.Inventors: Timothy Hindle, Steven Hadden, Torey Davis
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Patent number: 8678323Abstract: Embodiments of a launch lock assembly are provided, as are embodiments of a spacecraft isolation system including one or more launch lock assemblies. In one embodiment, the launch lock assembly includes first and second mount pieces, a releasable clamp device, and an axial gap amplification device. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement; and, when actuated, releases the first and second mount pieces from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device normally residing in a blocking position wherein the gap amplification device obstructs relative axial motion between the first and second mount pieces. The axial gap amplification device moves into a non-blocking position when the first and second mount pieces are released from clamped engagement to increase the range of axial motion between the first and second mount pieces.Type: GrantFiled: February 28, 2012Date of Patent: March 25, 2014Assignee: Honeywell International Inc.Inventors: Tim Daniel Barber, Timothy Hindle, Ken Young, Torey Davis
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Publication number: 20130221163Abstract: Embodiments of a launch lock assembly are provided, as are embodiments of a spacecraft isolation system including one or more launch lock assemblies. In one embodiment, the launch lock assembly includes first and second mount pieces, a releasable clamp device, and an axial gap amplification device. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement; and, when actuated, releases the first and second mount pieces from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device normally residing in a blocking position wherein the gap amplification device obstructs relative axial motion between the first and second mount pieces. The axial gap amplification device moves into a non-blocking position when the first and second mount pieces are released from clamped engagement to increase the range of axial motion between the first and second mount pieces.Type: ApplicationFiled: February 28, 2012Publication date: August 29, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Tim Daniel Barber, Timothy Hindle, Ken Young, Torey Davis
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Publication number: 20130067931Abstract: Embodiments of a gas turbine engine assembly including a strut-based vibration isolation mount are provided, as are embodiments of a method for producing such a gas turbine engine assembly. In one embodiment, the gas turbine engine assembly includes a gas turbine engine and a vibration isolation mount. The vibration isolation mount includes, in turn, at least one three parameter axial strut having a first end attached to the gas turbine engine and having a second, opposing end configured to be attached to the airframe. The three parameter axial strut is tuned to minimize the transmission of vibrations from the gas turbine engine to the airframe during operation of the gas turbine engine.Type: ApplicationFiled: September 21, 2011Publication date: March 21, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Timothy Hindle, Brian Cottrell, Torey Davis
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Publication number: 20130051981Abstract: Gas turbine engine, broadband damping systems, and methods for producing broadband-damped gas turbine engine are provided. In one embodiment, the gas turbine engine includes an engine case, a rotor assembly mounted within the engine case for rotation about a rotational axis, and a broadband damping system disposed between the rotor assembly and the engine case. The broadband damping system includes a first set of three parameter axial dampers angularly spaced around the rotational axis, and a second set of three parameter axial dampers angularly spaced around the rotational axis and coupled in parallel with the first set of three parameter axial dampers. The first and second sets of three parameter axial dampers are tuned to provide peak damping at different rotational frequencies to increase the damping bandwidth of the broadband damping system during operation of the gas turbine engine.Type: ApplicationFiled: August 26, 2011Publication date: February 28, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Timothy Hindle, Steven Hadden, Torey Davis
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Patent number: 7985162Abstract: A signal torque module assembly (STMA) is provided for use within a control moment gyroscope of the type that includes a rotor assembly. The STMA comprises a torque module assembly (TMA), which includes: (i) a TMA housing, (ii) a torque motor coupled to the TMA housing, and (iii) a gear train coupled to the TMA housing and mechanically coupling the torque motor to the rotor assembly. A signal module assembly is coupled to the TMA housing, and an elongated connector electrically couples the signal module assembly and the rotor assembly. The elongated connector extends through the gear train.Type: GrantFiled: March 19, 2008Date of Patent: July 26, 2011Assignee: Honeywell International Inc.Inventors: Paul Buchele, Torey Davis
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Publication number: 20090235765Abstract: A signal torque module assembly (STMA) is provided for use within a control moment gyroscope of the type that includes a rotor assembly. The STMA comprises a torque module assembly (TMA), which includes: (i) a TMA housing, (ii) a torque motor coupled to the TMA housing, and (iii) a gear train coupled to the TMA housing and mechanically coupling the torque motor to the rotor assembly. A signal module assembly is coupled to the TMA housing, and an elongated connector electrically couples the signal module assembly and the rotor assembly. The elongated connector extends through the gear train.Type: ApplicationFiled: March 19, 2008Publication date: September 24, 2009Applicant: Honeywell International Inc.Inventors: Paul Buchele, Torey Davis