Patents by Inventor Thomas A. Pollack

Thomas A. Pollack 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).

  • Hollow fan blade constrained layer damper
    Patent number: 10557353
    Abstract: A fan blade having a damping system is provided. The fan blade comprising: a fan blade body having one or more compartments within the fan blade body; a damping material located within at least one of the one or more compartments; one or more partial ribs originating at the fan blade body and extending into at least one of the one or more compartments, wherein each of the one or more partial ribs terminate at a distal end; and one or more damping plates, wherein each of the one or more damping plates are attached to a distal end of a partial rib, wherein the damping material is located between the damping plate and the fan blade body.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: February 11, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eric W. Malmborg, Thomas A. Pollack
  • Blade with damping structures
    Patent number: 10465715
    Abstract: A blade of a gas turbine engine may comprise a cavity defined, at least partially, by a first interior surface of the blade and by a second interior surface of the blade. A first rib and a second rib may extend from the first interior surface. A third rib may extend from the second interior surface and may be located between the first rib and the second rib. A bulkhead rib may traverse the cavity and may separate the cavity into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: November 5, 2019
    Assignee: GOODRICH CORPORATION
    Inventor: Thomas A. Pollack
  • BLADE WITH DAMPING STRUCTURES
    Publication number: 20190113052
    Abstract: A blade of a gas turbine engine may comprise a cavity defined, at least partially, by a first interior surface of the blade and by a second interior surface of the blade. A first rib and a second rib may extend from the first interior surface. A third rib may extend from the second interior surface and may be located between the first rib and the second rib. A bulkhead rib may traverse the cavity and may separate the cavity into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity.
    Type: Application
    Filed: October 18, 2017
    Publication date: April 18, 2019
    Applicant: GOODRICH CORPORATION
    Inventor: Thomas A. Pollack
  • HOLLOW FAN BLADE CONSTRAINED LAYER DAMPER
    Publication number: 20190112931
    Abstract: A fan blade having a damping system is provided. The fan blade comprising: a fan blade body having one or more compartments within the fan blade body; a damping material located within at least one of the one or more compartments; one or more partial ribs originating at the fan blade body and extending into at least one of the one or more compartments, wherein each of the one or more partial ribs terminate at a distal end; and one or more damping plates, wherein each of the one or more damping plates are attached to a distal end of a partial rib, wherein the damping material is located between the damping plate and the fan blade body.
    Type: Application
    Filed: October 18, 2017
    Publication date: April 18, 2019
    Inventors: Eric W. Malmborg, Thomas A. Pollack