Ceramic blade with tip seal
Patent
·
OSTI ID:516915
The present gas turbine engine includes a disc assembly defining a disc having a plurality of blades attached thereto. The disc has a preestablished rate of thermal expansion and the plurality of blades have a preestablished rate of thermal expansion being less than the preestablished rate of thermal expansion of the disc. A shroud assembly is attached to the gas turbine engine and is spaced from the plurality of blades a preestablished distance forming an interface there between. Positioned in the interface is a seal having a preestablished rate of thermal expansion being generally equal to the rate of thermal expansion of the plurality of blades. 4 figs.
- Research Organization:
- Solar Turbines Inc
- Sponsoring Organization:
- USDOE, Washington, DC (United States)
- DOE Contract Number:
- AC21-93MC30246
- Assignee:
- Solar Turbines Inc., San Diego, CA (United States)
- Patent Number(s):
- US 5,653,579/A/
- Application Number:
- PAN: 8-555,686
- OSTI ID:
- 516915
- Country of Publication:
- United States
- Language:
- English
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