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The wall static pressure changes are shown from the rotor inlet to exit in figure 34 for the design speed line and at vari- ous pressure ratios. Compared with rotor I, rotor II had less of a static pressure drop as the flow went from the inducer to the exducer; there was less acceleration occurring in the flow for the shorter rotor II. Discussion The efficiencies measured in this investigation were 2 to 3 percent below the design intent. To address this discrepancy, analytical studies were conducted by using the compact tur- bine experiment to predict the losses; the results are presented in references 2 and 3. The analytical study shows that the major losses are caused by incidence and clearance. Further studies are needed to determine how to avoid some losses due to the clearance between the blades and the backface where the turbine is scalloped. Another area to study is the incidence loss due to the leading edge geometry. When the compact turbine designs are compared with state- of-the-art turbines described in the literature, the compact tur- bines met and, in most cases, exceeded the efficiencies meas- ured thus far for conventional turbines. For example, figure 35 shows state-of-the-art radial turbine data (refs. 7 to 13), which were in the 3119-hp range. pressure ratio, specific work, efficiency, work factor, and torque. The results of the stator and rotor exit surveys were presented along with the rotor exit rake data. The results obtained from the three configurations were nearly identical. The efficiencies measured for these designs were approxi- mately 2 to 3 points lower than the design intent. However, when the compact turbine designs were compared with the state-of-the-art turbines reported in the literature, the compact turbines met and, in most cases, exceeded the efficiencies demonstrated to date. This investigation showed that a relatively shorter high- work radial inflow turbine rotor can achieve the high efficien- cies relative to high-work baseline design turbines. A size reduction of up to 52 percent in axial length, 4 percent in radial width, and 40 percent in weight can be achieved with- out a major efficiency penalty. Lewis Research Center National Aeronautics and Space Administration Cleveland, Ohio, January 11, 1995 _' o "G _o o E .85 I- Ref.9 .90 .80 .80 Ref.10 Ref.13 Ref. 11 zx ......... t ...................................... .90 1.00 1.10 1.20 .30 Ref.8 ® AA• Ref. 7 RotorI Ref. 12 ix Ref. 12 z_ Work factor, gdAh_/Ut2 Figure 35.--Comparison of compact turbines to state-of the-artturbinesdescribedinliterature. Summary of Results An experimental performance evaluation of three compact radial inflow turbine stage configurations was conducted. The overall performance was presented in terms of mass flow, RotorII 17PDF Image | Aerodynamic Radial Inflow Turbine Rotors
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