Modeling of Ice Accretion and Shedding In Turbofan Engines With Mixed Phase/Glaciated (Ice Crystal) Conditions

Icing codes for the assessment of ice accretion with super-cooled liquid droplets are an integral part of the certification process for new commercial gas turbine engines. These codes are used to perform critical point analyses within the icing flight envelope and to make comparisons with FAA certification testing conducted on the ground or in altitude facilities. The advent of new regulations requiring the assessment of mixed phase/glaciated icing conditions requires new capabilities to enable these codes to assess the ice crystal threat. This paper provides details of requirements for modeling of ice crystal processing by the engine and the contribution of ice crystals to the thermodynamics of mixed phase ice accretion and shedding. These details are applied to the TSIICE engine icing analysis and are compared with available data. The TSIICE code is appropriate for this use since it has proven capabilities for simultaneously determining the accretion and shedding of ice on engine airfoils and other critical surfaces within an engine. It is applicable to both rime and glaze ice accretion and includes a predictor for internal compressor air flow parameters (pressure, temperature and Mach number) at the desired engine power and flight/test condition.

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See papers presented at 2007 SAE Aircraft and Engine Icing International Conference, September 2007, Seville, SPAIN, Session: Aircraft Engine Icing - Design, Analysis, and Modeling Tools for Supercooled Liquid, Crystals & Hail

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