Patent ID: 8047773

Claim:
A support apparatus for a shroud of a gas turbine, the gas turbine comprising a rotating shaft defining a radial direction perpendicular thereto, the apparatus comprising: an outer shroud block comprising a coupling connectable to a casing of the gas turbine; a shroud component comprising a forward flange and an aft flange, the shroud component attached to the outer shroud block via the forward flange and the aft flange; a damper disposed between the outer shroud block and the shroud component with a translational degree of freedom between the damper and the outer shroud block that defines a direction of motion of the damper, the direction of motion forming an angle greater than zero degrees relative to the radial direction of the gas turbine; a biasing element disposed within the outer shroud block, the biasing element in operable connection between the outer shroud block and the shroud component via the damper, a bias force of the biasing element directed along the direction of motion of the damper; a first pin extendible through an aperture in the forward flange or the aft flange, and a deformation interface between a head of the first pin and the outer shroud block.