Abstract
The counter-rotating turbine technology is one of the potential technical measures to improve the performance of aero-engine. Inspired by axial-flow counter-rotating turbine, this paper applied the counter-rotating turbine technology to the centrifugal turbine and carried out the aerodynamic design of the 1 + 1/2 counter-rotating centrifugal turbine stage by theoretical analysis using the air ideal gas as the working fluid. Then the blade profile of 1 + 1/2 counter-rotating centrifugal turbine was designed based on the velocity triangle obtained from theoretical analysis. At last, 1 + 1/2 counter-rotating centrifugal turbine was numerically analyzed and compared with the two-stage co-rotating centrifugal turbine under the same thermal parameters. The results show that the 1 + 1/2 counter-rotating centrifugal turbine has 12.0% less maximum diameter and 1.57% higher efficiency than the two-stage co-rotating centrifugal turbine.
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