By Jan Roskam
A useful encyclopedia of old plane information, layout equations and strategies.
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Additional info for Airplane Design Parts I-VII
Ceramic Materials for Energy Applications II -43 SiC-Coated HTR Fuel Particle Performance n tv Φ < o T- C Λ Ul 3 " "c U. 0 ummmum FRJ2K15/1 * 3 » . / 800 & ^ EZ 700 FRJ2K1S2 FRJ2-K13/1&2 900 1000 1100 1200 1300 1400 Temperature (°C) Figure 7: Accumulated fast neutron fluence (xlO25 neutrons/m2, E>16 O) versus operating temperature for LEU U0 2 TRISO coated fuel particles in accelerated irradiation tests conducted in European MTRs prior to 2000 and in the AVR reactor up to December 1988. 1000 1100 1200 1300 Temperature (°C) Figure 8: Fuel burnup (% FIMA) versus operating temperature for LEU U02 TRISO coated fuel particles in accelerated irradiation tests conducted in European MTRs prior to 2000 and in AVR.
L. , 329-333, 56-65 (2004). 3 R. , 64, 155170(2004). 4 A. Kohyama, S. M. Dong and Y. Katoh, "Development of SiC/SiC Composites by Nano-Infiltration and Transient Eutectic (NITE) Process," Ceramic Engineering and Science Proceedings. ,311-318 (2000). 5 S. M. Dong, Y. Katoh and A. ,23, 1223-1231 (2003). 6 J. A. DiCarlo, "Microstructural Optimization of High Temperature SiC/SiC Composites," Proceedings of the 5lh International Conference on High Temperature Ceramic Matrix Composites (HTCMC5), p. 187-192, The American Ceramics Society, Ohio (2004).
7 g/cm3 (90 % achievement of theoretical density). TRISO particles were well distributed in SiC matrix and took no significant damages like cracks and fractures. Thermal conductivity of 40 vol% TRISO particles exhibited excellent values up to 1200 °C , owing to the high thermal conductivity values of inert SiC matrix without TRISO particles itself. REFERENCES 1 "Ceramic Matrix Composites -Microstructure, Properties and Applications-," edited by I. M. Low. Woodhead Publishing, Abington, England, 2006.
Airplane Design Parts I-VII by Jan Roskam