Conceptual design of ceramic matrix composites turbine blade for typical turbofan engine

被引：0
|
作者：
Shi D. [1 ]
Wang Z. [1 ]
Liu C. [1 ]
Zhang W. [1 ]
Chen M. [1 ]
Yang X. [1 ]
机构：
[1] School of Energy and Power Engineering, Beihang University, Beijing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 02期
关键词：
aerodynamic design; ceramic matrix composites (CMCs); deformation; strength analysis; structural design; turbine blade;
D O I：
10.13224/j.cnki.jasp.20220513
中图分类号：
学科分类号：
摘要：
For the purpose of technological progress for ceramic matrix composites (CMCs) turbine blade design in advanced aero-engines，based on main performance parameters of typical turbofan engine，and according to the forward turbine blade design process，a conceptual design method was established from aerodynamic design to structural design finally to deformation and strength analysis，and a CMCs low pressure turbine rotor blade was designed，which was solid without cooling. In the conceptual design method，strength was taken as the major constraint，aero-engine thrust and specific fuel consumption taken as inputs， and model of turbine blade body taken as output. The simulation results indicated that aerodynamic performance， strength and vibration performance of the designed blade under design conditions satisfy the design requirements. Reserve factor of safety reached 1.8 and the external load level of the turbine disk was estimated to be reduced by 50%，proving the feasible application of CMCs on advanced aero-engines. Turbine efficiency increased approximately 0.98%—1.17%，which demonstrated the potential of CMCs to promote the performance of high-temperature components in advanced aero-engines. © 2023 BUAA Press. All rights reserved.
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页码：431 / 444
页数：13
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