| Title |
CERAMIC REGENERATOR SYSTEMS DEVELOPMENT PROGRAM. FINAL REPORT
|
| Accession No |
00343870 |
| Authors |
Fucinari, C A; Rahnke, C J; Rao, VDN; Vallance, J K |
Corp. Authors
/ Publisher |
Department of the Navy  ; Ford Motor Company ; Department of Energy
|
| Publication Date |
19801000 |
| Description |
263 p.
|
| Abstract |
This is the final report for the NASA/Ford Ceramic Regenerator Systems Development Program. It describes all of the results obtained in this program, which started October 1, 1976 and was completed December 31, 1979. Tasks within this program included: core durability testing at 800 exp 0 C (1472 exp 0 F); core durability testing at 1000 exp 0 C (1832 exp 0 F); material screening tests; aerothermodynamic performance; design studies of advanced regenerator systems; ceramic thermal stability tests; manufacturing cost studies; and core material and design specifications. Technical progress in each task is reported. Approximately 77,296 core h of engine durability test at 800 exp 0 C (1472 exp 0 7) were completed under this program. Turbine engine durability tests on aluminum silicate (AS) regenerator cores show that this material is relatively impervious to chemical attack. Fourteen cores of this material have each accumulated over 5000 h of engine test at 800 exp 0 C (1472 exp 0 F), and five cores have each attained the durability objective of 10,000 h with a minimal amount of chemical attack damage. Little problem has been encountered with the elastomer which bonds the ring gear to the regenerator matrix for thick-wall AS or magnesium aluminum silicate (MAS) assemblies. The elastomer cut from an assembly after 7000 h of engine test, shows little sign of aging. Twelve different regenerators have been tested at 1000 exp 0 C (1832 exp 0 F) and this sample has accumulated 28,834 h at this temperature. AS and MAS cores showed good mechanical integrity and no signs of chemical nor thermal distress after operation at this temperature. It was concluded that MAS matrix materials provide the best resistance to chemical attack in the engine |
| TRT Terms |
Aluminum compounds ; Ceramic materials ; Cores (Specimens) ; Corrosion ; Corrosion resistance ; Costs ; Design ; Durability ; Elastomers ; Failure ; High temperature ; Magnesium compounds ; Manufacturing ; Materials ; Materials tests ; Performance tests ; Regenerators ; Reliability ; Silicates ; Technology assessment ; Testing ; Thermal stresses ; Turbine engines ; Vehicles ; Wear |
| Other Terms |
Aging; Aluminium silicates; Chemical attack; Cores; Gas turbine engines; Heat recovery; Materials testing; Performance testing; Very high temperature |
| Subject Areas |
H34 GENERAL MATERIALS; H53 VEHICLE CHARACTERISTICS; I35 Miscellaneous Materials; I91 Vehicle Design and Safety |
| Contract Number |
AI01-76CS31037 |
| Report Number |
DOE/NASA/0008-12; NASA-CR-165139 |
| Availability |
National Technical Information Service Order Number: DE81023765
|
| Document Source |
National Technical Information Service
Source Data: u8123
|
| TRIS Files |
HRIS |
| Database |
TRIS Online |
TRT
