Tham khảo tài liệu 'gas turbines part 10', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | 214 Gas Turbines Rubechini F. Marconcini M. Arnone A. Maritano M. Cecchi S. 2008 . The impact of gas modeling in the numerical analysis of a multistage gas turbine. Journal of Turbomachinary Vol. 130 pp. 021022-1 - 021022-7 April 2008. Vieira L. Matt C. Guedes V. Cruz M. Castelloes F. 2008 . Optimization of the operation of a complex combined-cicle cogeneration plant using a professional process simulator. Proceedings of IMECE2008. ASME International mechanical Engineering Congress and Exposition pp. 787-796 October 31-November 6 2008 Boston Massachusetts USA. Watanabe M. Ueno Y. Mitani Y. Iki H. Uriu Y. Urano Y. 2008 . Developer of a dynamical model for customer s gas turbine generator in industrial power systems. 2nd. IEEE International conference on power and energy PECon 08 . December 1-3 pp. 514-519 2008 Johor Baharu Malaysia. Zhu Y. Frey . 2007 . Simplified performance model of gas turbine combined cycle systems. Journal of Energy Engineering. Vol. 133 No. 2 Jun 2007 pp. 82-90 ISSN 0733-9402. 9 Life Prediction of Gas Turbine Materials Xijia Wu Institute for Aerospace Research National Research Council Canada 1. Introduction The advance of gas turbine engines and the increase in fuel efficiency over the past 50 years relies on the development of high temperature materials with the performance for the intended services. The cutaway view of an aero engine is shown in Fig. 1. During the service of an aero engine a multitude of material damage such as foreign object damage erosion high cycle fatigue low cycle fatigue fretting hot corrosion oxidation creep and thermomechanical fatigue will be induced to the components ranging from fan compressor sections up front to high pressure HP and low pressure LP turbine sections at the rear. The endurance of the gas turbine engine to high temperature is particularly marked by the creep resistance of HP turbine blade alloy. Figure 2 shows the trend of firing temperature and turbine blade alloy capability Schilke 2004 . .
