Ceramic Composites Regeneratively Cooled Rocket Engine Components

Recently Refractory Composites, Inc. (RCI) successfully demonstrated a new class of materials, actively cooled ceramic composites. RCI proposes to extend this technology to Refeneratively Cooded C/SiC composites for rocket engine hot section components such as combusters and nozzles. In order to contain the high combustion pressures, 2500 psi and higher, in high performance engines, RCI will develop a hybrid composite material system having high strength and low gas permeabilities. The regeneratively cooled ceramic composite operating at hot surface temperatures greter than 2500 degrees F has large pay-offs as a result of a significant weight reductions due to decreases in component mass and descreased wet fraction associated with higher operating temperatures. Furthermore, with wall temperatures of 2500 degrees F for C/SiC as opposed to 800 degrees F, there is a reduction in total hydrogen cooling mass required per unit time, thus reduced turbo pump engine cycle losses. The primary goal of the Phase I program will be to demonstrate the technical and economic feasibility of regeneratively cooled C/SiC body of revolution rocket components operating at combustion pressures above 2500 psi. In Phase I material and thrust chamber testing will be performed. Pratt & Whitney will assist in materials characterization, component design and, during the Phase II program, larger scale component testing.