Study on Blade Bend Optimization of Aircraft Engine

Abstract:

Whether blade profile of aircraft engine is reasonable depends on whether the surface pneumatic distribution given is satisfactory[1,2].In the experiments of optimization design,we discover that the design results are too dependent on surface velocity distribution with the following problems:The first is that the blade bend does not meet the requirements;The second is that blade thickness does not meet the requirements;The third is that the profiles of suction and pressure surfaces are not superposed very well at the leading and following edges with mouth open or cross;The fourth is that some situations of non-design behaviour are not taken into account. In this paper,these issues of blade bend optimization are discussed.

• Periodical: Advanced Materials Research (Volumes 538-541)
• Pages: 516-519
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.538-541.516
• Online since: June 2012
• Authors: Wang Sheng Liu, Chun Lai Hu, Yan Sun, Guo Dong Shi, Xing Long Liu
• Keywords: Aircraft Engine, Bend Optimization, Blade Profile

References

[1] Schnorenberg D G.M.S. Thesis,Naval Postgraduate school,AD-A313561,1996.

[2] Garth V H,Denis J H,David G S,et al. ASME Paper 98 -GT- 422,12p.

[3] Ronghui Cheng ,Yongxing Zhong, Ruqun Yun. Journal of Aerospace Power/Hangkong Dongli Xuebao 1993,8(3):221-224.

[4] Bhaskar Roy,Ujjwal K Saha. ASME Paper 95-CTP-41,7pp.