Abstract
*† This paper offers a comparison between turbine-compressor matching and combustor models for the Air Turborocket (ATR). A description of the Air Turborocket flowpath and its operation is given. Multiple component-level models of increasing complexity are explored. These models are incorporated into a thermodynamic cycle analysis and are compared on the basis of thrust and specific impulse performance. This analysis is performed over a range of Mach numbers representative of the first stage of a two-stage-toorbit launch vehicle. The results of this analysis verify that the ATR is able to provide higher thrust than a traditional turbojet, but with lower specific impulse. The advanced flowpath model demonstrates the importance of properly constraining the design of this engine, showing that the ATR performance degrades greatly above Mach 3. Higher-bypass ATR configurations, balancing increases in thrust and specific impulse, show the most promise.
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