Experimental Investigation of a Bleed Air Ice Protection System

The work presented in this paper is part of a long-term research program to explore methods for improving bleed air system performance. Another objective of this research is to provide detailed experimental data for the development and validation of simulation tools used in the design and analysis of bleed air systems. A business jet wing was equipped with an inner-liner hot air ice protection system and was extensively instrumented for documenting system thermal performance. The wing was tested at the NASA Glenn Icing Research Tunnel (IRT) for representative in-flight icing conditions. Data obtained include bleed air supply and exhaust flow properties, wing leading edge skin temperatures, temperatures and pressures in the interior passages of the bleed air system, flow properties inside the piccolo tube, photos of run back ice shapes and ice shape traces. Selected experimental results for a warm hold icing condition are presented in this paper. The results include dry and wet bleed air system data and demonstrate the effect of piccolo hot-air mass flow and hot-air temperature on system performance and runback ice accretions.

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See papers presented at 2007 SAE Aircraft and Engine Icing International Conference, September 2007, Seville, SPAIN, Session: In-flight Ice Protection Systems - Part I

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