Journal of the Korea Institute of Military Science and Technology (한국군사과학기술학회지)

The Korea Institute of Military Science and Technology (한국군사과학기술학회)
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Preliminary Aerodynamic Design of 13:1 Pressure Ratio Axial-Centrifugal Compressor

13:1의 압축비를 갖는 축류-원심형 압축기의 기본 공력설계

  • Published : 2003.07.01
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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.

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