No abstract

The paper describes some of the design solutions that were adopted in the realization of a small two shaft, counterrotating turbine rig. The turbine, for a small space engine technology upper stage liquid propellant rocket turbo pump system, was only 100mm tip diameter with a correspondingly small annulus height. Detailed flow measurements were provided by 3 axis actuators at inlet and outlet of the working section. Torque and Power were measured on each shaft using Radio Frequency (R.F.) telemetry torquemeters. A modular design allowed the rig to be rebuilt rapidly in one and two stage configurations with different blade sets. This enabled the effect of changing turbine configurations to be studied.