Abstract
An air turbo rocket (ATR) is an air-breathing propulsion system that possesses design, performance, and operation characteristics of the turbojet, ramjet, and rocket in a single unit. In order to assess the capabilities of the ATR, an analysis of a representative liquid oxygen - liquid hydrogen engine is carried out. Complete analysis of the intake, fan, gas generator, turbine and combustion chamber has been carried out for two representative flight conditions, namely, a low speed of Mach number 2 and altitude of 6000m and a high speed of Mach number 3 and altitude of 9000m. The study is aimed at finding oxygen to fuel (O/F) ratio for maximum specific impulse. An off -design analysis of the ATR designed at Mach 1 is also carried out. Finally, to realize these specific impulse values, basic dimensions of the turbo machinery, number of stages for a tip turbine and a conventional inline turbine are proposed. Comparison is made between an ATR operating on different fuels in terms of the number of turbine stages required and the specific impulse variation with different afterburner fuels.
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