Support apparatus and method for ceramic matrix composite turbine bucket shroud
A shroud support method and apparatus for a ceramic component of a gas turbine having: an outer shroud block having a coupling to a casing of the gas turbine; a spring mass damper attached to the outer shroud block and including a spring biased piston extending through said outer shroud block, wherein the spring mass damper applies a load to the ceramic component; and the ceramic component has a forward flange and an aft flange each attachable to the outer shroud block.
1. A method for testing a ceramic stationary component of a gas turbine comprising:
a. securing an outer shroud block to a casing of the gas turbine;
b. attaching a forward flange and an aft flange of the component to the outer shroud;
c. loading the component between the forward flange and the aft flange by applying a bias force to the component with a spring mass damper which comprises a spring and a distinct damper having a different structural shape than the spring, wherein the bias force is applied to the component between the forward flange and the aft flange;
d. damping relative movement between the component and the outer shroud by the distinct damper, and
e. exposing the component to a hot gas stream in the gas turbine.
2. A method as in claim 1 wherein the loading of the component is by applying the bias force to a surface of the component opposite to a surface of the component exposed to the hot gas stream.
3. A method as in claim 1 wherein the bias force is applied along a direction substantially normal to the hot gas stream.
4. A method as in claim 1 wherein the component is a melt-infiltrated ceramic matrix composite inner shroud for a row of turbine buckets of a gas turbine.
5. A method as in claim 1 further comprising directing cooling air through the outer shroud and mass spring damper.
6. A method as in claim 1 wherein the distinct damper is coaxial with the spring, wherein the spring is a coil spring.
7. A method as in claim 1 wherein the spring and the distinct damper apply a spring force and a damping force, respectively, wherein the spring force is aligned with the damping force along a direction of the relative movement.
8. A method for testing a ceramic stationary component of a gas turbine comprising:
a. securing an outer shroud block to a casing of the gas turbine;
b. attaching a forward flange and an aft flange of the component to the outer shroud;
c. loading the component between the forward flange and the aft flange by applying a bias force to the component with a spring mass damper which comprises a coil spring and a distinct damper, wherein the damper has a different structural shape than the spring,
d. damping relative movement between the component and the outer shroud by the distinct damper, and
e. exposing the component to a hot gas stream in the gas turbine.
9. A method as in claim 8 wherein the loading of the component is by applying the bias force to a surface of the component opposite to a surface of the component exposed to the hot gas stream.
10. A method as in claim 8 wherein the bias force and a damping force are coaxial.
11. A method as in claim 8 wherein the component is a melt-infiltrated ceramic matrix composite inner shroud for a row of turbine buckets of a gas turbine.
12. A method as in claim 8 further comprising directing cooling air through the outer shroud and mass spring damper.
13. A method as in claim 8 wherein the spring and the distinct damper apply a spring force and a damping force, respectively, wherein the spring force is aligned with the damping force along a direction of movement of the component.
14. A method for testing a ceramic stationary component of a gas turbine comprising:
a. securing an outer shroud block to a casing of the gas turbine;
b. attaching a forward flange and an aft flange of the component to the outer shroud;
c. loading the component between the forward flange and the aft flange by applying a bias force to the component with a spring mass damper which comprises a coil spring and a distinct damper,
d. damping relative movement between the component and the outer shroud by the spring mass damper, wherein the distinct damper includes a shaft extending through the coil spring, and
e. exposing the component to a hot gas stream in the gas turbine.