Patent ID: 6261058
Filing Date: 2001-07-17
Classification: F01D,F05D

Abstract:
A stationary blade segment for an integrated segment construction including a plurality of stationary blades for a gas turbine comprising:a blade having outer and inner ends, an outside shroud joined to the outer end, and an inside shroud joined to the inner end, each shroud having an end face portion adapted to abut an end face portion of an adjacent stationary blade segment shroud; anda plate seat connector affixed at each end face portion of the inside shroud and the outside shroud, each plate seat connector extending outwardly away from its corresponding shroud and comprising a flat seat face at an outer portion thereof, each of said plate seat connectors being adapted to receive a bolt for securing the seat face thereof in face to face contact with the seat face of an adjacent plate seat connector, the seat face of each said plate seat connector being non-contiguous with respect to the end face of the end face portion of the shroud to which said connector is affixed.