Foam Ceramic Nozzle Inserts.

摘要

Eight nozzle inserts were fabricated from United Technology Center's foam ceramic composites to define the operational limitations of these materials when used in liquid rocket engines employing either N2O4/N2H4-UDMH or LF2/N2H4 Blend propellants. The nozzle inserts consisted of the following: Condition 1 -- (N204/N2H4-UDMH); Al203 + SiO2 fibers (two nozzles), ZrO2 + SiO2 fibers (two nozzles); Condition 2 - - (LF2/N2H4 Blend); ZrO2 + C fibers (two nozzles), and ZrC + C fibers (two nozzles). Thermal and mechanical property tests were conducted on the ceramic foam composites. The objective was to supply data for an Air Force computer program to predict materials performance in rocket engines, and to afford a basis for evaluating nozzle erosion from the firings in this program. The test firing were conducted by the Air Force Rocket Propulsion Laboratory, Research and Technology Division, Edwards, California. The classified results and posttest analyses are included in this report. (Author)