Dedekind, MOHarris, LE2007-06-122007-06-121996-01-03Dedekind, MO and Harris, LE. 1996. Evaluation of premature failure of a gas turbine component. International Journal of pressure vessels and piping, vol. 66, 3 January, pp 59-760308-0161http://hdl.handle.net/10204/591Copyright: 1996 Elsevier Sciences LtdA case study of certain gas turbine stator vanes which fail prematurely is presented, with a view to determining whether operational procedure might have caused the failures. The engines had been operated from a ‘hot-and-high’ environment, and this could have contributed to the failures. Computational fluid dynamics (CFD) techniques were employed in order to obtain an accurate design point thermal history. The resulting convection boundary conditions were then interpolated over a finite element mesh. Transient thermal and stress analyses were performed. At the same time, micro structural analyses of the service-exposed material were carried out to estimate the maximum temperature seen by the component. These showed that higher than expected vane metal temperatures were experienced. Emphasis was placed on the procedures outlined in the USAF Engine Structural Integrity Program, since little detail was known about the actual engine operating histories.enLife assessmentMAR-M509Gas turbine enginesFinite element analysisComputational fluid dynamicsArticleDedekind, M., & Harris, L. (1996). Evaluation of premature failure of a gas turbine component. http://hdl.handle.net/10204/591Dedekind, MO, and LE Harris "Evaluation of premature failure of a gas turbine component." (1996) http://hdl.handle.net/10204/591Dedekind M, Harris L. Evaluation of premature failure of a gas turbine component. 1996; http://hdl.handle.net/10204/591.TY - Article AU - Dedekind, MO AU - Harris, LE AB - A case study of certain gas turbine stator vanes which fail prematurely is presented, with a view to determining whether operational procedure might have caused the failures. The engines had been operated from a ‘hot-and-high’ environment, and this could have contributed to the failures. Computational fluid dynamics (CFD) techniques were employed in order to obtain an accurate design point thermal history. The resulting convection boundary conditions were then interpolated over a finite element mesh. Transient thermal and stress analyses were performed. At the same time, micro structural analyses of the service-exposed material were carried out to estimate the maximum temperature seen by the component. These showed that higher than expected vane metal temperatures were experienced. Emphasis was placed on the procedures outlined in the USAF Engine Structural Integrity Program, since little detail was known about the actual engine operating histories. DA - 1996-01-03 DB - ResearchSpace DP - CSIR KW - Life assessment KW - MAR-M509 KW - Gas turbine engines KW - Finite element analysis KW - Computational fluid dynamics LK - https://researchspace.csir.co.za PY - 1996 SM - 0308-0161 T1 - Evaluation of premature failure of a gas turbine component TI - Evaluation of premature failure of a gas turbine component UR - http://hdl.handle.net/10204/591 ER -