Patents by Inventor David L. Joyce

David L. Joyce 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).

  • Publication number: 20190336264
    Abstract: Embolic protection devices can be used to enhance the treatment of heart conditions such as, but not limited to, heart failure and aortic valve stenosis. For example, this document describes percutaneously-deployable intravascular embolic protection devices and methods for their use. The embolic protection devices can be used to capture and remove embolic materials that could otherwise cause adverse patient effects.
    Type: Application
    Filed: December 1, 2017
    Publication date: November 7, 2019
    Applicant: Mayo Foundation for Medical Education and Research
    Inventors: Atta Behfar, David L. Joyce, Mandeep Singh, Andre Terzic
  • Patent number: 10444014
    Abstract: An angular sensor. The angular sensor includes a Coriolis vibratory gyroscope (CVG) resonator, configured to oscillate in a first pair of normal modes including a first normal mode and a second normal mode and a second pair of normal modes including a third normal mode and a fourth normal mode. The angular sensor further includes a coarse readout circuit configured to drive the first pair of modes, measure the motion of the first pair of modes, and derive from the measured motion of the first pair of modes a coarse measurement of an angular rate of the resonator. The angular sensor further includes and a fine readout circuit configured to derive a measurement of the difference between the true angular rate of the resonator and the coarse measurement.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: October 15, 2019
    Assignee: HRL Laboratories, LLC
    Inventors: Logan D. Sorenson, Raviv Perahia, David T. Chang, Randall L. Kubena, Deborah J. Kirby, Hung Nguyen, Richard J. Joyce
  • Patent number: 5752674
    Abstract: A system is provided for reducing ice mass on an aircraft engine. A compressor inlet temperature and pressure sensor measures total temperature and total pressure at the inlet to the engine compressor. An ice shield is provided, wherein a plurality of wedge portions has multiple protrusions for promoting ice formation in multiple locations. The ice shield is separable from the sensor with which it interfaces. The ice shield comprises straight angle wedge shapes and curved surfaces to separate and minimize ice accretion in desired locations. The mass of each resultant ice formation is reduced to a size that the compressor inlet blades can withstand without deformation.
    Type: Grant
    Filed: August 21, 1996
    Date of Patent: May 19, 1998
    Assignee: General Electric Company
    Inventors: John S. Mears, Ronald A. Bulow, David L. Joyce, Kevin H. Kast
  • Patent number: 5242265
    Abstract: A system for changing pitch in aircraft propfans is disclosed, in which a motor, located at a stationary position, changes pitch of the blades by of a gear train. Three features of the system are that a feather brake can override the motor and drive the blades toward feather; a unison brake can prevent pitch from undergoing excursions toward fine pitch when propeller speed exceeds a limit; and the motor is non-rotating in the absence of pitch change. A pair of such systems can be used in a counterrotating propfan system, in order to independently change pitch of the propfans.
    Type: Grant
    Filed: July 23, 1990
    Date of Patent: September 7, 1993
    Assignee: General Electric Company
    Inventors: Petr Hora, Thomas C. Hermans, David E. Bulman, Edwin K. Miller, Thomas G. Wakeman, David L. Joyce
  • Patent number: 5213471
    Abstract: The invention concerns a system for controlling an aircraft propeller. A hydraulic motor controls pitch of the propeller blades. The propeller blades are characterized by the absence of feather-inducing counterweights. An overspeed governor senses when propeller speed exceeds a limit, and, in response, assumes control of the hydraulic motor and drives the blades toward a coarsened pitch position, which reduces the propeller speed. In another form of the invention, a mechanical brake can override the hydraulic motor and mechanically retard a rotating gear, which causes the propeller blades to move toward a coarsened pitch.
    Type: Grant
    Filed: September 4, 1990
    Date of Patent: May 25, 1993
    Assignee: General Electric Company
    Inventors: Edwin K. Miller, Robert L. Roberts, Petr Hora, David L. Joyce, John S. Mears
  • Patent number: 5012420
    Abstract: The invention concerns an active clearance control for controlling clearance between a turbine and a casing in a gas turbine aircraft engine.The invention calculates the instantaneous clearance between a turbine casing and a turbine rotor, based on temperature. Two temperatures are involved. First, a steady state temperature (SSTemp) is computed for the rotor and the casing. SSTemp is a predicted, future temperature, which will be attained when the engine reaches steady state operation. Each SSTemp is computed based on presently occurring engine operating conditions, such as selected temperatures, pressures, and rotational speeds.Changes which occur in the SSTemp's indicate the second temperatures, which are the instantaneous temperatures of the casing and rotor. These changes in SSTemp are caused by changes in the present operating conditions, which occur during engine acceleration and deceleration.
    Type: Grant
    Filed: March 31, 1988
    Date of Patent: April 30, 1991
    Assignee: General Electric Company
    Inventors: Roger C. Walker, Scott P. Reese, David L. Joyce, David A. Kastrup