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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Robert, J. Boyle Ankur, H. Parikh Vinod, K. Nagpal Michael, C. Halbig James, A. Dicarlo |
| Copyright Year | 2014 |
| Abstract | Through thickness, hoop, and spanwise component stresses were calculated for two Ceramic Matrix Composite (CMC) vane configurations. The analyses are for the first stage vane of a High Pressure Turbine. One configuration is for a vane with trailing edge ejection, and the other has no trailing edge ejection. The effects of analyzing separate pressure and thermal loads, as well as combining these loads, are examined. For the case without trailing edge ejection the effects of variations in the stiffness modulus are given. Results are discussed for the midspan region as well as for the entire span. Pressure loads were determined assuming a mainstream gas and coolant pressure of 50 atm. Thermal loads were determined assuming a gas temperature of 2141°K(3394°F), and a maximum Environmental Barrier Coating temperature of 1756°K(2700°F). The desired maximum CMC temperature was 1589°C(2400°F). |
| Sponsorship | International Gas Turbine Institute |
| File Format | |
| ISBN | 9780791845752 |
| DOI | 10.1115/GT2014-27136 |
| Volume Number | Volume 6: Ceramics; Controls, Diagnostics and Instrumentation; Education; Manufacturing Materials and Metallurgy |
| Conference Proceedings | ASME Turbo Expo 2014: Turbine Technical Conference and Exposition |
| Language | English |
| Publisher Date | 2014-06-16 |
| Publisher Place | Düsseldorf, Germany |
| Access Restriction | Subscribed |
| Subject Keyword | High pressure (physics) Ceramic matrix composites Temperature Coolants Stiffness Coating processes Coatings Pressure Turbines Stress |
| Content Type | Text |
| Resource Type | Article |
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