FENSAP-ICE: Ice Accretion in Multi-stage Jet Engines

Ice accretion in aircraft engine components has raised safety and performance concerns. When flying in hazardous weather conditions, engines can ingest a mix of iced and liquid particles that can potentially result in a dangerous build-up on the forward components of the engines. The ice can then shed from the fan, spinner or IGV, and may cause mechanical damage and performance losses to downstream components. In order to cost-effectively replicate such an environment, a three-dimensional quasi-steady numerical approach is developed to model both rotating and static components, and their interaction. An inter- component mixing-plane approach, along with stagnation and radial equilibrium boundary conditions, has been implemented within FENSAP-ICE allowing the treatment of multi- stage unequal-pitch blade rows via a finite element interpolation method and proper circumferential averaging. The approach is first validated for the well-documented Aachen turbine and then used on a compressor stage to obtain impingement locations of supercooled droplets and ice shapes.

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