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http://dx.doi.org/10.5139/JKSAS.2008.36.9.898

A Study of the Second Stage Effect on a Partially Admitted Small Turbine  

Cho, Chong-Hyun (경상대학교 항공공학과 대학원)
Cho, Bong-Soo (경상대학교 항공공학과 대학원)
Choi, Sang-Kyu (한국기계연구원, 지능형정밀기계연구본부)
Cho, Soo-Yong (경상대 항공기부품기술연구센터)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.36, no.9, 2008 , pp. 898-906 More about this Journal
Abstract
A tested turbine consists of two stages, and an axial-type and a radial-type turbine are applied to the first and second stage, respectively. The mean diameter of the axial-type turbine rotor is 70 mm, and the outer diameter of the radial-type turbine is 68mm at the inlet. In this experiment, an axial-type turbine, two different radial-type turbines, and three different nozzle flow angles are applied to find the optimal design parameters. To compare the turbine performance, the net specific output torque is evaluated. The test results show that the nozzle flow angle on the first stage is a more important parameter than other design parameters for partially admitted small turbines to obtain high operating torque. For a 3.4% partial admission rate, the net specific output torque is increased by 13% with the addition of a radial-type rotor to the second stage when the turbine operates at $75^{\circ}$ nozzle flow angle.
Keywords
Partial Admitted Turbine; Micro Turbine; Turbine Performance; Nozzle Flow Angle;
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