Monorotor for Air Turborocket (ATR) Engine

Recent CFDRC studies have demonstrated the advantages of developing back to back radial/mixed flow monorotor technology fully integratable between an ATR tailored solid fuel gas generator (SFGG) and a high heat release combustion chamber. To achieve an ATR Isp over 1500 seconds, the turbine half will utilize an optimized SFGG effluent gas and compactly discharge into the combustor fuel injection assembly. The compressor half will be designed to withstand excessive inlet distortion, and provide a compromise between maximum pressure ratio (to minimize combustor volume) and flow (to maximize engine Isp). Design speed will be selected to accommodate ATR engine turndown ratio requirements associated with vehicle boost, cruise, and loiter requirements. Phase I work proposed includes: a. documentation of related work and promising IM solid propellants; b. ATR component dimension/weight specification in an engine layout; c. preliminary monorotor design and analysis (including CFD simulation); d. monorotor performance definition using ATR engine cycle analysis; e. supporting thermal and mechanical stress analysis (Campbell and Goodman diagrams) for the monorotor assembly; and f. development of a Phase II fabrication, assembly, and test plan. During Phase II, the same team; i.e., CFDRC, Sundstrand Power Systems, and Atlantic Research Corporation, will demonstrate the monorotor in an ATR engine assembly.