Spray forming composite combustion chamber structures

摘要

In future, innovative high-performance propulsion systems will accelerate hypersonic aircraft to speeds of more than Mach 10. This requires new engine types which are essentially based on the functional principle of the rocket motor. These so-called Rocket-Based Combined Cycle Engines (RBCCE) comprise a combination of rocket engines and a downstream Laval nozzle section with an afterburner and adjustable Laval geometry. The thermomechanical loads on the variable linear flap structure following afterburning are extremely high and thus necessitate an actively cooled system. Innovative materials and process technologies are required in order to produce the complex structures cost-effectively.