Evaluation of Spiral Wound Ribbon Structures for Transpiration/Film Cooling.

摘要

This program included studies in heat transfer, fluid flow, stress analysis, materials and metallurgical evaluation, fabrication studies including tooling development, and the design, fabrication, and test of rocket thrust chambers operating at 1300 to 1800 psia chamber pressure with storable propellants. Spiral wound ribbon nozzle and chamber-nozzle structures were designed and fabricated for test. Serious problems were encountered during fabrication with high-strength materials. Tests were conducted with uncooled heat-sink thrust chambers to evaluate performance of injectors. Thrust chamber heat flux values were obtained in tests with instrumented uncooled engines. A test conducted with a spiral wound ribbon nozzle resulted in almost immediate failure of the water-cooled chamber. A test of the spiral wound ribbon chamber-nozzle was terminated after about 4 seconds of operation. Analysis of the test results indicated that burn-through occurred initially in the chamber section due to inadequate coolant flow. The nozzle and exit cone were excessively overcooled. Results indicate that major modifications are required to achieve suitable coolant flow distribution under these conditions of operation. (Author)