한국유체기계학회 논문집 (The KSFM Journal of Fluid Machinery)
- 제2권1호
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- Pages.88-95
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- 1999
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- 2287-9706(pISSN)
헬리콥터용 터보샤프트엔진 2단 축류압축기 개량설계
Modification of a Two Stage Axial Compressor of a Turboshaft Engine for Helicopters
- 발행 : 1999.03.01
초록
This paper introduces the part of efforts to develop a derivative type turboshaft engine from an existing baseline engine for multi-purpose helicopters aiming at 4000 kg of take-off weight for 10-12 passengers. As a first step in meeting the development goal of increasing the output power from 720 hp to 840hp with minimum modification, a two stage axial compressor was redesigned to obtain the higher pressure ratio by removing the inlet guide vane and increasing the chord length. As a result, a two stage axial compressor was designed to facilitate a flow rate of 3.04 kg/s, a pressure ratio of 2.01 and an adiabatic efficiency of