Equivalent Heat Load Test on Hot Aircraft Engine Components
DOI:
https://doi.org/10.24425/afe.2023.144277Abstract
The paper presents the assumptions and methodology for investigating equivalent heat load testing of hot aircraft engine components. The basic heat loads occurring in an aircraft engine during aircraft flight are characterised. Diagrams of the proposed heat loads are presented, together with the number of cycles, and a test bench is characterised and shown to enable equivalent heat load testing of aircraft engine components.References
[1] Hejwowski, T., Weroński, A. (2000). Manufacture of wear-resistant coatings. Lublin: Politechnika Lubelska. (in Polish).
[2] Research stand in WSK PZL Rzeszów.
[3] Chaur, - Jeng Wang, & Jiaun, - Sheng Lin (2002). The oxidation of MAR M247 superalloy with Na2SO4 coating. Materials Chemistry and Physics. 76, 123-129. DOI: 10.1016/S0254-0584(01)00527-2.
[4] Goebel, J.A., Petit, F.S. & Howard, G.W. (1973). Mechanism for the hot corrosion of nickel base alloys. Metallurgical Transactions. 4, 261-270. https://doi.org/10.1007/BF02649626.
[5] Su, C.Y., Lih, W.C., Chou, C.P. & Tsai, H.C. (2001). Activated diffusion brased repair for IN 738 hot section components of gas turbine. Journal of Materials Processing Technology. 115(3), 326-332.
