Chapter 29. Densification of a Thick Disk Preform with Silicon Carbide Matrix by CVI Process
- John B. Wachtman Jr
Published Online: 26 MAR 2008
Copyright © 1991 The American Ceramic Society, Inc.
Proceedings of the 15th Annual Conference on Composites and Advanced Ceramic Materials, Part 2 of 2: Ceramic Engineering and Science Proceedings, Volume 12, Issue 9/10
How to Cite
Huynh, T., Burkland, C. V. and Bustamante, B. (2008) Densification of a Thick Disk Preform with Silicon Carbide Matrix by CVI Process, in Proceedings of the 15th Annual Conference on Composites and Advanced Ceramic Materials, Part 2 of 2: Ceramic Engineering and Science Proceedings, Volume 12, Issue 9/10 (ed J. B. Wachtman), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470313848.ch29
- Published Online: 26 MAR 2008
- Published Print: 1 JAN 1991
Print ISBN: 9780470375105
Online ISBN: 9780470313848
A ceramic matrix composite (CMC) bladed rotor was fabricated by a chemical vapor infiltration (CVI) process. The demonstration article was based on an uncooled design for an expendable turbine engine. The rotor employed a 2-D polar woven Nicalon© fiber preform. The preform disk was 2.30 cm (0.90 in.) thick with an inner hub diameter of 4.4 cm (1.75 in.) and an outside diameter of 14 cm (5.5 in.). The Nicalon© fiber preform was first coated with an interface layer of pyrolytic carbon (PyC). After the PyC coating, the disk preform was densified to 90 ± 2% of the theoretical density with the silicon carbide (SiC) matrix by CVI. After completing the densification process, the composite disk was machined to net shape. The machining operation included conventional surface grinding and computerized ultrasonic machining of the blades. The evaluation of the CMC rotor included NDE, microstructuralanalysis, microntechankalmaterials modeling, finite element disk analysis, and a cold spin test.