The proposed Propulsion Thermal Management Module (PTMM), a key subsystem of the aircraft Integrated Thermal Management System (ITMS), is designed to supply cooling to all propulsion system components, including the engine, exhaust nozzle, fuel controls(FADEC), lubrication, and hydraulic systems. The propulsion thermal management module would be matched to cooling requirements for a wide range of aircraft propulsion systems by adding or increasing the size of basic components. The propulsion thermal management module is designed to increase efficiency of turboramjet engines by optimizing the distribution of fuel coolant between the turbomachinery and ramjet coolant systems to maximize operating temperatures. Cooling requirements of the turboramjet are unique in that during climb the highest heat load is on the turbomachinery and at high Mach cruise the highest heat load is in the ramjet section. A typical multiple engine aircraft would have a propulsion module for each engine matched to the aircraft mission requirements. The proposed prototype design, simulation, and testing effort will result in demonstration of a propulsion thermal management module suitable for high Mach aircraft applications (LRSA, RTA, JSF)
