1. A comparison of damage tolerance behaviour of two different nickel base super alloys under a turbine standard spectrum loads
- Author
-
Sharanagouda G. Malipatil, C. M. Manjunatha, M. Manjuprasad, Anuradha Nayak Majila, and D. Chandru Fernando
- Subjects
Superalloy ,Cyclic stress ,Amplitude ,Materials science ,Tension (physics) ,Waveform ,Composite material ,Paris' law ,Damage tolerance ,Turbine - Abstract
In this investigation, the damage tolerance behavior of two different aero-engine materials i.e., GTM718 and GTM720 nickel base super alloys subjected to a turbine standard spectrum loads was experimentally determined and compared. Compact tension (CT) specimens as per ASTM test standard specifications were cut and prepared from the forged discs of these materials. Fatigue crack growth (FCG) tests were conducted using CT specimens in a 100 kN servo-hydraulic universal test machine at ambient temperature and lab air atmosphere. Constant amplitude cyclic fatigue loads were applied on CT specimen to initiate a pre-crack of about 2.0 mm in length from the notch root. Further, the fatigue crack was propagated under standard cold-TURBISTAN spectrum load sequence. The crack length was measured by compliance method as well as by using optical traveling microscope at regular intervals of completion of load blocks. Loading waveform employed during the test was triangular with a frequency of 2 Hz i.e., four reversals per second. The average fatigue crack growth life under turbine standard spectrum loads observed was observed to be lower in GTM718 when compared to GTM 720 material. The measured crack growth life was about 48 blocks and 38 blocks in GTM 720 and GTM 718 respectively. It was clear from these experiments that GTM720 is more damage tolerant than GTM718 material.
- Published
- 2021