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Journal of the Korea Institute of Military Science and Technology 2003;6(2):83-94.
Preliminary Aerodynamic Design of 13:1 Pressure Ratio Axial-Centrifugal Compressor
13:1의 압축비를 갖는 축류-원심형 압축기의 기본 공력설계
김원철
국방과학연구소
Abstract
Preliminary aerodynamic design of a compressor is carried out to meet the design requirements which are pressure ratio of 13, air mass flow rate of 4 ㎏/s and rotational speed of 45,000 rpm. The compressor type is chosen as an axial-centrifugal compressor from the design requirements which is suitable for a medium power class turboprop or turboshaft engine. Its overall isentropic efficiency is estimated to be 0.796 and its surge margin to be 20% exceeding the design requirement. This paper summarizes the aerodynamic design details including the design procedures and the results of the axial -centrifugal compressor.
Key Words: Aerodynamic Design, Axial-centrifugal Compressor, Turboshaft Engine
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