Matrix crack initiation in ceramic matrix composites Part I: Experiments and test results

1992 ◽  
Vol 44 (3) ◽  
pp. 257-269 ◽  
Author(s):  
Michel W. Barsoum ◽  
Pramod Kangutkar ◽  
A.S.D. Wang
Keyword(s):  
Crack Initiation ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Matrix Crack ◽  
Matrix Composites ◽  
Test Results

Conditions for matrix crack deflection at an interface in ceramic matrix composites

1998 ◽  
Vol 250 (2) ◽  
pp. 291-302 ◽  
Author(s):  
E. Martin ◽  
P.W.M. Peters ◽  
D. Leguillon ◽  
J.M. Quenisset
Keyword(s):  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Crack Deflection ◽  
Matrix Crack ◽  
Matrix Composites

Ceramic Matrix Composites for Rocket Engine Turbine Applications

1993 ◽  
Vol 115 (1) ◽  
pp. 64-69 ◽  
Author(s):  
T. P. Herbell ◽  
A. J. Eckel
Keyword(s):  
Rocket Engine ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Matrix Composites ◽  
Test Results ◽  
Test Rig ◽  
Heating Rates ◽  
Isothermal Exposure ◽  
Monolithic Ceramics ◽  
Exposure Evaluation

A program to establish the potential for introducing fiber-reinforced ceramic matrix composites (FRCMC) in future rocket engine turbopumps was instituted in 1988. A brief summary of the overall program (both contract and in-house research) is presented. Tests at NASA Lewis include thermal upshocks in a hydrogen/oxygen test rig capable of generating heating rates up to 2500°C/s. Post-thermal upshock exposure evaluation includes the measurement of residual strength and failure analysis. Test results for monolithic ceramics and several FRCMCs are presented. Hydrogen compatibility was assessed by isothermal exposure of monolithic ceramics in high-temperature gaseous hydrogen plus water vapor.

scholarly journals Ceramic Matrix Composites for Rocket Engine Turbine Applications

1992 ◽  
Author(s):  
Thomas P. Herbell ◽  
Andrew J. Eckel
Keyword(s):  
Rocket Engine ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Matrix Composites ◽  
Test Results ◽  
Test Rig ◽  
Heating Rates ◽  
Isothermal Exposure ◽  
Monolithic Ceramics ◽  
Exposure Evaluation

A program to establish the potential for introducing fiber reinforced ceramic matrix composites (FRCMC) in future rocket engine turbopumps was instituted in 1987. A brief summary of the overall program (both contract and in-house research) is presented. Tests at NASA Lewis include thermal upshocks in a hydrogen/oxygen test rig capable of generating heating rates up to 2500 °C/sec. Post thermal upshock exposure evaluation includes the measurement of residual strength and failure analysis. Test results for monolithic ceramics and several FRCMC are presented. Hydrogen compatibility was assessed by isothermal exposure of monolithic ceramics in high temperature gaseous hydrogen plus water vapor.

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