Patents by Inventor James Charles Gautreau

James Charles Gautreau 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).

  • Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
    Patent number: 7165944
    Abstract: A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.
    Type: Grant
    Filed: January 21, 2005
    Date of Patent: January 23, 2007
    Assignee: General Electric Company
    Inventors: James Charles Gautreau, Nicholas Francis Martin, Chris A. Rickert
  • Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
    Patent number: 7121803
    Abstract: A blade of an turbomachine having an airfoil with a leading edge and a root; a base attached to the root of the airfoil; a dovetail portion of the base engageable with disk; a slot in the base generally parallel to a face of the base extending between opposite sides of the base, and a vibration adsorbing insert snuggly fitted into the slot.
    Type: Grant
    Filed: December 20, 2004
    Date of Patent: October 17, 2006
    Assignee: General Electric Company
    Inventors: James Charles Gautreau, Nicholas Francis Martin, Chris A. Rickert
  • Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
    Patent number: 6902376
    Abstract: A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.
    Type: Grant
    Filed: December 26, 2002
    Date of Patent: June 7, 2005
    Assignee: General Electric Company
    Inventors: James Charles Gautreau, Nicholas Francis Martin
  • Undercut leading edge for compressor blades and related method
    Publication number: 20040213672
    Abstract: A compressor blade includes an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion, the undercut defined by a narrow entry slot opening into a rearward transverse groove.
    Type: Application
    Filed: April 25, 2003
    Publication date: October 28, 2004
    Inventors: James Charles Gautreau, Nicholas Francis Martin, Chris A. Rickert
  • Undercut leading edge for compressor blades and related method
    Patent number: 6769877
    Abstract: A compressor blade includes an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion.
    Type: Grant
    Filed: October 18, 2002
    Date of Patent: August 3, 2004
    Assignee: General Electric Company
    Inventors: Nicholas Francis Martin, James Charles Gautreau
  • Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
    Publication number: 20040126239
    Abstract: A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.
    Type: Application
    Filed: December 26, 2002
    Publication date: July 1, 2004
    Inventors: James Charles Gautreau, Nicholas Francis Martin
  • Undercut leading edge for compressor blades and related method
    Publication number: 20040076521
    Abstract: A compressor blade includes an airfoil portion having a leading edge, a radially inner attachment portion, and a platform between the airfoil portion and the attachment portion, wherein material is removed from the attachment portion to form an undercut at a front face thereof to thereby provide an overhang radially inward of the platform and leading edge of the airfoil portion.
    Type: Application
    Filed: October 18, 2002
    Publication date: April 22, 2004
    Inventors: Nicholas Francis Martin, James Charles Gautreau