Volume 19, Issue 10 (October 2019)                   Modares Mechanical Engineering 2019, 19(10): 2409-2418 | Back to browse issues page

XML Persian Abstract Print


Download citation:
BibTeX | RIS | EndNote | Medlars | ProCite | Reference Manager | RefWorks
Send citation to:

Shirzadi S, Badri-kouhi E, Adibnazari S. Effect of Contact Geometry on the Slip Amplitude and Contact Pressure in Fretting Fatigue of a Turbine Blade Root. Modares Mechanical Engineering 2019; 19 (10) :2409-2418
URL: http://mme.modares.ac.ir/article-15-21496-en.html
1- Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
2- Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran , adib@sharif.ir
Abstract:   (3565 Views)

Turbine blades are exposed to mechanical and thermal stresses due to their operation in critical conditions that lead to various damages such as fatigue and wear. These factors reduce the blades life cycle by accelerating the cracking process. In this paper, the effects of three geometric parameters including the contact length, the contact angle, and the surface friction coefficient on relative slip amplitude and contact pressure values in the turbine blade root were investigated using a two-dimensional finite element model. Comparing the results of the analysis with the actual blade damages by use of scanning electron microscopy shows acceptable consistency between predicted damage site and the actual blade damages. The results of the blade analysis indicate that by moving from the top of the contact edge to the bottom, the contact pressure increases gradually and its maximum occurs near the lower edge of the contact. According to the results, the prescribed increments in the coefficient of friction, the contact angle, and the length of contact, respectively decrease the slip amplitude by 26%, 19%, and 10% and also decrease the contact pressures by 35%, 15%, and 5%. In addition, increasing contact angle and coefficient of friction increase the opening region length at the upper edge on both sides of the blade root. While increasing the contact length has no considerable effect on the length of this region.


Full-Text [PDF 1406 kb]   (4713 Downloads)    
Article Type: Original Research | Subject: Aerospace Structures
Received: 2018/05/29 | Accepted: 2019/02/23 | Published: 2019/10/22

References
1. Hattori T, Kien VT, Yamashita M. Fretting fatigue life estimations based on fretting mechanisms. Tribology International. 2011;44(11):1389-1393. [Article] [DOI:10.1016/j.triboint.2010.10.020]
2. Kermanpur A, Sepehri Amin H, Ziaei-Rad S, Nourbakhshnia N, Mosaddeghfar M. Failure analysis of Ti6Al4V gas turbine compressor blades. Engineering Failure Analysis. 2008;15(8):1052-1064. [Article] [DOI:10.1016/j.engfailanal.2007.11.018]
3. Shi L, Wei DS, Wang YR, Tian AM, Li D. An investigation of fretting fatigue in a circular arc dovetail assembly. International Journal of Fatigue. 2016;82(Pt 2):226-237. [Article] [DOI:10.1016/j.ijfatigue.2015.07.025]
4. ASTM International. ASTM E2789-10(2015) standard guide for fretting fatigue testing [Internet]. West Conshohocken: ASTM International; 2015 [Unknown cited]. Available from: https://www.astm.org/Standards/E2789.htm. [Article]
5. Hills DA, Nowell D. Mechanics of fretting fatigue. Dordrecht: Kluwer Academic Publishers; 1994. pp. 9-122. [Article] [DOI:10.1007/978-94-015-8281-0_2]
6. Rajasekaran R, Nowell D. Fretting fatigue in dovetail blade roots: Experiment and analysis. Tribology International. 2006;39(10):1277-1285. [Article] [DOI:10.1016/j.triboint.2006.02.044]
7. Kanth PS. 2D & 3D FE analysis of fir-tree joints in aeroengine discs [Dissertation]. Toronto: University of Toronto; 1998. [Article]
8. Ruiz C, Boddington PHB, Chen KC. An investigation of fatigue and fretting in a dovetail joint. Experimental Mechanics. 1984;24(3):208-217. [Article] [DOI:10.1007/BF02323167]
9. Ruiz C, Nowell D. Designing against fretting fatigue in aeroengines. European Structural Integrity Society. 2000;26:73-95. [Article] [DOI:10.1016/S1566-1369(00)80043-6]
10. Papanikos P, Meguid SA, Stjepanovic Z. Three-dimensional nonlinear finite element analysis of dovetail joints in aeroengine discs. Finite Elements in Analysis and Design. 1998;29(3-4):173-186. [Article] [DOI:10.1016/S0168-874X(98)00008-0]
11. Conner BP, Nicholas T. Using a dovetail fixture to study fretting fatigue and fretting palliatives. Journal of Engineering Materials and Technology. 2003;128(2):133-141. [Article] [DOI:10.1115/1.2172272]
12. Golden PJ. Development of a dovetail fretting fatigue fixture for turbine engine materials. International Journal of Fatigue. 2009;31(4):620-628. [Article] [DOI:10.1016/j.ijfatigue.2008.03.017]
13. Golden PJ, Nicholas T. The effect of angle on dovetail fretting experiments in Ti‐6Al‐4V. Fatigue & Fracture of Engineering Materials & Structures. 2005;28(12):1169-1175. [Article] [DOI:10.1111/j.1460-2695.2005.00956.x]
14. Golden PJ, Calcaterra JR. A fracture mechanics life prediction methodology applied to dovetail fretting. Tribology International. 2006;39(10):1172-1180. [Article] [DOI:10.1016/j.triboint.2006.02.006]
15. Poursaeidi E, Salavatian M. Fatigue crack growth simulation in a generator fan blade. Engineering Failure Analysis. 2009;16(3):888-898. [Article] [DOI:10.1016/j.engfailanal.2008.08.016]
16. Hahn Y, Cofer JI. Design study of dovetail geometries of turbine blades using abaqus and isight. ASME Proceedings Structures and Dynamics Parts A and B. 2012;7:11-20. [Article] [DOI:10.1115/GT2012-68566]
17. Anandavel K, Prakash RV. Effect of three-dimensional loading on macroscopic fretting aspects of an aero-engine blade-disc dovetail interface. Tribology International. 2011;44(11):1544-1555. [Article] [DOI:10.1016/j.triboint.2010.10.014]

Add your comments about this article : Your username or Email:
CAPTCHA

Send email to the article author


Rights and permissions
Creative Commons License This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.