Patents by Inventor Stephen J. Yee

Stephen J. Yee 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).

  • Turbine blade internal cooling configuration
    Patent number: 8172533
    Abstract: A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.
    Type: Grant
    Filed: May 14, 2008
    Date of Patent: May 8, 2012
    Assignee: United Technologies Corporation
    Inventors: Sandra S. Pinero, Edward F. Pietraszkiewicz, Bryan P. Dube, Stephen J. Yee, Ryan Shepard Levy, Mohamed Hassan, Domenico Valerio, Scott D. Hartmann
  • NOZZLE SEGMENT WITH REDUCED WEIGHT FLANGE
    Publication number: 20110236199
    Abstract: A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.
    Type: Application
    Filed: March 23, 2010
    Publication date: September 29, 2011
    Inventors: Russell J. Bergman, Stephen J. Yee, Leonard A. Bach, Joseph W. Bridges, JR., Lawrence J. Willey, Brandon W. Spangler
  • Turbine blade internal cooling configuration
    Publication number: 20090285684
    Abstract: A cooled airfoil includes a concave pressure wall extending radially from a base to a tip of the airfoil, a convex suction wall connected to the concave pressure wall at a leading edge and a trailing edge spaced axially from the leading edge, and a plurality of cooling channels formed between the concave pressure wall and the convex suction wall and configured to receive a cooling fluid supply from the base of the airfoil. The cooling channels include a leading edge channel extending radially from the base toward the tip, a trailing edge channel extending radially from the base toward the tip and in flow communication with a plurality of trailing edge apertures adapted to exhaust cooling fluid to the exterior of the airfoil, a serpentine cooling circuit including a plurality of channels, and a dedicated up-pass channel extending radially from the base toward the tip between the leading edge channel and the forward most channel of the plurality of channels in the serpentine cooling circuit.
    Type: Application
    Filed: May 14, 2008
    Publication date: November 19, 2009
    Applicant: United Technologies Corporation
    Inventors: Sandra S. Pinero, Edward F. Pietraszkiewicz, Bryan P. Dube, Stephen J. Yee, Ryan Shepard Levy, Mohamed Hassan, Domenico Valerio, Scott D. Hartmann