Ceramic Matrix Composites (CMCs) have been proposed for use as lightweight hot structures in scramjet combustors. Previous studies have calculated significant weight savings by utilizing CMCs (active and passive) versus actively cooled metallic scramjet structures. Both a carbon/carbon (C/C) and a carbon/carbon-silicon carbide (C/C-SiC) material fabricated by DLR (Stuttgart, Germany) are being considered for use in a passively cooled combustor design for Hypersonic International Flight Research Experimentation (HIFiRE) 8, a joint Australia / Air Force Research Laboratory hypersonic flight program, expected to fly at Mach 7 for approximately 30 sec, at a dynamic pressure of 55 kilopascals. Flat panels of the DLR C/C and C/C-SiC materials were installed downstream of a hydrogen-fueled, dual-mode scramjet combustor and tested for several minutes at conditions simulating flight at Mach 5 and Mach 6. Gaseous hydrogen fuel was used to fuel the scramjet combustor. The test panels were instrumented with embedded Type K and Type S thermocouples. Zirconia felt insulation was used during some of the tests to reduce heat loss from the back surface and thus increase the heated surface temperature of the C/C-SiC panel approximately 177 C (350 F). The final C/C-SiC panel was tested for three cycles totaling over 135 sec at Mach 6 enthalpy. Slightly more erosion was observed on the C/C panel than the C/C-SiC panels, but both material systems demonstrated acceptable recession performance for the HIFiRE 8 flight.
Testing of DLR C/C-SiC and C/C for HIFiRE 8 Scramjet Combustor
2014
14 pages
Report
No indication
English
Composite Materials , Aircraft , Test Facilities & Equipment , Ceramic matrix composites , Carbon-silicon carbide composites , Supersonic combustion ramjet engines , Combustion chambers , Materials tests , High temperature tests , Hypersonic flight , Engine testing laboratories , Enthalpy , Rectangular panels , Temperature measurement , Pressure measurement , Testing time , Zirconium oxides , Insulation , Thickness , Scanning electron microscopy
Testing of DLR C/C-SiC and C/C for HIFiRE 8 Scramjet Combustor (AIAA 2014-3089)
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