Gas turbine shroud support apparatus

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 melt-infiltrated ceramic matrix composite inner shroud component comprising a forward flange and an aft flange, the melt-infiltrated ceramic matrix composite inner shroud component 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 melt-infiltrated ceramic matrix composite inner 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;
• and
• a biasing element disposed within the outer shroud block, the biasing element in operable connection between the outer shroud block and the melt-infiltrated ceramic matrix composite inner shroud component via the damper, a bias force of the biasing element directed along the direction of motion.

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 aft flange or the forward flange, the first pin comprising a retention aperture;
• and
• a retention pin disposed within the retention aperture of the first pin.

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 of the ceramic component,
• a deformation interface between a head of the first pin and the outer shroud block;
• a second pin extendible through an aperture in the aft flange or the forward, the second pin comprising a retention aperture;
• and
• a retention pin disposed within the retention aperture of the second pin.