한국유체기계학회 논문집 (The KSFM Journal of Fluid Machinery)

한국유체기계학회 (Korean Society for Fluid machinery)
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차세대 터보프롭 항공기용 복합재 최신 프로펠러 설계 및 해석

The Design and Analysis of Composite Advanced Propeller Blade for Next Generation Turboprop Aircraft

  • 최원 (한국항공우주산업(주) 고정익비행성능팀) ;
  • 김광해 (한국항공우주산업(주) 고정익비행성능팀) ;
  • 이원중 (한국항공우주연구원 항공안전기술개발사업단)
  • 투고 : 2012.02.23
  • 심사 : 2012.11.01
  • 발행 : 2012.12.01
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초록

The one way fluid structure interaction analysis on advanced propeller blade for next generation turboprop aircraft. HS1 airfoil series are selected as a advanced propeller blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point. Blade sweep is designed based on the design mach number and target propulsion efficiency. The aerodynamic characteristics of the designed Advanced propeller were verified by CFD(Computational Fluid Dynamic) and showed the enhanced performance than the conventional propeller. The skin-foam sandwich structural type is adopted for blade. The high stiffness, strength carbon/epoxy composite material is used for the skin and PMI(Polymethacrylimide) is used for the foam. Aerodynamic load is calculated by computational fluid dynamics. Linear static stress analysis is performed by finite element analysis code MSC.NASTRAN in order to investigate the structural safety. The result of structural analysis showed that the design has sufficient structural safety. It was concluded that structural safety assessment should incorporate the off-design points.

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참고문헌

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