Finite Element Formulation for Prediction of Over-speed and burst-margin limits in Aero-engine disc
Maruthi B H1, M. Venkatarama Reddy2, K. Channakeshavalu3
1Prof. Maruthi B H, Prof. & Head, Dept. of Mech. Engg, East West Institute of Technology, Bangalore, Inida.
2Dr. K Chennakeshavalu, Principal, , East West Institute of Technology, Bangalore, Inida.
3Dr. M Venkata Rama Reddy, Dept. of Mech. Engg. BIT, Bangalore, India.
Manuscript received on July 01, 2012. | Revised Manuscript received on July 04, 2012. | Manuscript published on July 05, 2012. | PP: 172-176| Volume-2, Issue-3, July 2012. | Retrieval Number: C0743062312 /2012©BEIESP
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© The Authors. Published By: Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: Turbo-machinery disks are heavy, highly stressed components used in gas turbine mainly due to over speed and operating temperatures. The experimental burst test is always time consuming and very expensive. Hence the objective this work was to develop finite element (FE) prediction to find over-speed and burst-margin limits. The FE method for the thermal and mechanical analysis is used for the determination of the over-speed and burst margin limit for high-speed aero-engine turbine disc for the speed between 10,000 rpm to 22,000 rpm at variable temperatures. The result shows that the magnitude of the tangential stress components is higher than that of the radial stress components for all the discs under variable temperature distribution. The tangential stress components are higher at inner surface and decreases toward outer surface. The burst margin speed was predicted as per formula and obtained for 18,500, 19,000 and more than 22,000 rpm for thermal + blade load + centrifugal load, thermal + centrifugal load and only centrifugal load respectively.
Keywords: Gas Turbine Disc, Over-speed, Burst Margin.