Patents by Inventor Daniel M. Eshak

Daniel M. Eshak 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: 20120148383
    Abstract: A vane structure for a gas turbine engine. The vane structure includes a radially outer platform and a radially inner platform, and an airfoil having an outer wall extending radially between the outer platform and the inner platform. A cooling passage is defined within the outer wall and has a plurality of radially extending channels. An outer end turn structure is located at the outer platform to conduct cooling fluid in a chordal direction between at least two of the channels. The outer end turn structure includes an enlarged portion wherein the enlarged portion is defined by an enlarged dimension, in a direction transverse to the chordal direction, between the at least two channels.
    Type: Application
    Filed: December 14, 2010
    Publication date: June 14, 2012
    Inventors: Paul J. Gear, Brian J. Wessell, Daniel M. Eshak
  • Publication number: 20120063908
    Abstract: A turbine vane for a turbine machine comprising an intermediate section having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a radial distance along a stacking axis that is normal to a centerline of the turbine machine and contain the X and Y values with Z value beginning at innermost aerodynamic point and the Z values represent a radial height of the vane and the X and Y values define the nominal airfoil profile at each radial height Z.
    Type: Application
    Filed: September 9, 2010
    Publication date: March 15, 2012
    Inventors: Alamgir T. Islam, Daniel M. Eshak, Paul J. Gear
  • Publication number: 20110243724
    Abstract: A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.
    Type: Application
    Filed: April 1, 2010
    Publication date: October 6, 2011
    Inventors: Christian X. Campbell, Jay A. Morrison, Allister W. James, Raymond G. Snider, Daniel M. Eshak, John J. Marra, Brian J. Wessell