Study about Ablative Coated Carbon Materials applied on Chambers of LRE

摘要

The Liquid Rocket Engine - LRE are extremely complex and versatile machines, involving several areas of knowledge for your development and manufacture. The machines like Turbopumps, Reducers, Regulators, Chambers and anothers are key elements in the performance and reliability of a LRE, mainly about mass and final performance. This paper describes the preliminary research effort to determine parameters for an hypothetical ablative engine, and its consequent project, with focus on the structural design of the chamber to be built, and the selection of materials for use in the construction of this chamber. The research was started with the development of a static small combustion chamber, designed in copper alloy C11000 and stainless steel AISI 304, with a removable nozzle support, seals and nozzle inserts. The tests performed in this static chamber is intended to test the behavior of carbon material inserts, coated or not, where the parameters of wear, erosion, generation of pores and irregular wear are extrapolated for use in design of larger combustion chambers. After analyzing the test data, it was possible to identify the strength and advantages of using these materials for the manufacture of combustion chambers, and these data extrapolation was made to preliminary design of a fligh ablative thrust chamber.