Journal of Thermal Spray Technology, vol. 18, issue 5-6 (2009) pp. 1004-1013
This paper reports recent research on abradable materials employed for aero-engine applications. Such thermal spray coatings are used extensively within the gas turbine, applied to the inner surface of compressor and turbine shroud sections, coating the periphery of the blade rotation path. The function of an abradable seal is to wear preferentially when rotating blades come into contact with it, while minimizing over-tip clearance and improving the efficiency of the engine. Thermal spraying of an abradable coating onto a substrate imparts two components of residual stress; rapid quenching stresses as the spray material cools on impact and stresses arising from differential thermal contraction. In-service thermal stresses are superimposed by the differential expansion of these bonded layers. The combination of the production and operation history will lead to thermal-mechanical fatigue damage within the abradable coating. The present paper will describe the numerical modeling and sensitivity analysis of the thermal spray process. The sensitivity of residual stresses (with varying material properties, coating/substrate thickness, Poisson’s ratio, and substrate temperature) predicted by the Tsui and Clyne progressive deposition model enabled identification of performance drivers to coating integrity. Selecting material properties that minimize in-service stresses is a crucial stage in advancing future abradable performance.
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