Ceramic turbine nozzle
A turbine nozzle and shroud assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components have a preestablished rate of thermal expansion greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes a plurality of segmented vane defining a first vane segment and a second vane segment, each of the first and second vane segments having a vertical portion, and each of the first vane segments and the second vane segments being positioned in functional relationship one to another within a recess formed within an outer shroud and an inner shroud. The turbine nozzle and shroud assembly provides an economical, reliable and effective ceramic component having a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the other component. 4 figs.
- Research Organization:
- Solar Turbines Inc
- DOE Contract Number:
- AC02-92CE40960
- Assignee:
- Solar Turbines Inc., San Diego, CA (United States)
- Patent Number(s):
- US 5,584,652/A/
- Application Number:
- PAN: 8-369,245
- OSTI ID:
- 415724
- Country of Publication:
- United States
- Language:
- English
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