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Characterization of ceramic matrix composite vane subelements subjected to rig testing in a gas turbine environment
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Robinson, R. Craig Thomas, David J. Calomino, Anthony Verrilli, Michael |
| Copyright Year | 2004 |
| Description | Vane subelements were fabricated from a silicon carbide fiber-reinforced silicon carbide matrix (SiC/SiC) composite. A cross-sectional slice of an aircraft engine metal vane was the basis of the vane subelement geometry. To fabricate the small radius of the vane's trailing edge using stiff Sylramic SiC fibers, a unique SiC fiber architecture was developed. A test configuration for the vanes in a high pressure gas turbine environment was designed and fabricated. Testing was conducted using a pressure of 6 atm and combustion flow rate of 0.5 kg/sec, and consisted of fifty hours of steady state operation followed by 102 2-minute thermal cycles. A surface temperature of 1320 C was obtained for the EBC-coated SiC/SiC vane subelement. This paper will briefly discuss the vane fabrication, test configuration, and results of the vane testing. The emphasis of the paper is on characterization of the post-test condition of the vanes. |
| File Size | 9141890 |
| Page Count | 7 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20050198903 |
| Archival Resource Key | ark:/13960/t8md3wh67 |
| Language | English |
| Publisher Date | 2004-05-12 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Ceramic Matrix Composites High Temperature Tests Fiber Composites Vanes Silicon Carbides Thermal Cycling Tests Engine Parts Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
