중형 항공기 고효율 경량화 복합재 프로펠러 블레이드의 설계 연구

Abstract

Recently, the need for developing the environmental and eco-friendly aircrafts with increased fuel efficiency is being emphasized as an eco-friendly requirement in response to high oil prices. Aircrafts take up 3-5% of the world’s carbon dioxide emission amount and the aircraft industry is placed at the top in the emission amount as a single industry. The amount of carbon dioxide being discharged in high altitude atmosphere is larger than that being discharged by every vehicle on the earth. Accordingly, it is necessary to develop the next-generation eco-friendly & high fuel efficiency engine technology to enhance the fuel efficiency and aerodynamic performance of aircrafts for the purpose of reducing carbon dioxide emission amount prior to collecting and dealing with air pollution substances being discharged. Many studies for advanced turboprop were performed. Among the previous studies, Roy H. Lange performed research about a review of advanced turboprop transport aircraft in 1986. F. Farassat et al. performed the study on advanced turboprop noise prediction based on recent theoretical results in 1987. This paper deals with the development of a high speed propeller noise prediction code at Langley Research Center. J. A. Liser et al. studied aeroacoustic design of a 6-bladed propeller in 1997. This paper show that tip mach number reduction is a very effective way of reducing noise levels, especially when the original mach number is nearly transonic. In 2006, Quentin R. Wald performed the study on aerodynamics of propellers. In this paper, the theory and the design of propellers of minimum induced loss is treated. In 1992, Takashi Yamane performed the study of aeroelastic tailoring analysis for advanced turbo propellers with composite blades. In this study, the aeroelastic model of advanced composite materials is proposed. Many studies have shown that the efficiency of advanced turboprop is higher than that of the current turbofan design. After many years of study, various aerodynamic design theories were proposed. However, little research work has been carried out to propose the design method of propeller structure. In this work, aerodynamic and structural designs of the propeller blade for an advanced turboprop aircraft, which will be used for a next generation regional commercial aircraft in Korea, are carried out. In the aerodynamic design, the parametric studies are performed to decide an optimum aerodynamic configuration having a specific HS1 series airfoil. In structural design, the proposed propeller blade uses the carbon/epoxy composite skin and spar and urethane foam core sandwich type structure, so-called skin-spar-foam sandwich, is adopted. In order to confirm the initially designed propeller using the netting rule and the rule of mixture, the structural analysis including stress, eigen value and buckling analyses is performed using finite element code, MSC. NASTRAN. To finalize the proposed propeller structure design, the prototype propeller is manufactured, tested and compared with the structural analysis results.