Scaling Evaluation of Ice-Crystal Icing on a Modern Turbofan Engine in PSL Using the COMDES-MELT code 2019-01-1920
This paper presents preliminary ice crystal icing (ICI) altitude scaling evaluation results of a Honeywell Uncertified Research Engine (HURE) that, featuring a hidden core design which keeps the core less exposed, was tested in the NASA Glenn Research Center Propulsion Systems Laboratory (PSL) during January of 2018. The engine was fitted with internal video cameras to observe various ice buildup processes at multiple selected locations within the engine compressor flow path covering the fan stator, the splitter lip/shroud/gooseneck, and the high pressure compressor (HPC) variable inlet guide vane (IGV) regions where potential ice accretion risk was pre-determined to occur by using NASA’s in-house 1-D engine icing risk assessment code COMDES-MELT. In addition for calculating possible scale test conditions at different selected altitudes numerous simulations of COMDES-MELT were run to determine potential inlet conditions that could lead to ice crystal accretion along the prescribed locations where the cameras were set up. These conditions were first simulated in the PSL to help select the reference baseline condition. Then possible scale test conditions were determined by best matching the following three icing related parameters of the reference condition: (1) the local air total wet bulb temperature, (2) the local ice crystal cloud melt ratio and (3) the engine fan face ice/water to air mass flux ratio of the ice crystal cloud at the selected ice accretion location. The individual digital images and the time-lapsed movies of ice buildup are used to help evaluate how closely the proposed icing scaling method could be used in a test facility like PSL to duplicate a reference ice crystal icing features observed at specific location inside a full scale engine at different scale altitudes. Some discussion on observed limitation for engine icing complete scaling application from the test campaign and needed improvement of the test facility both in operation, cloud calibration and measurement capability, and test condition controllability will be provided in the final paper.
Ohio Aerospace Institute
International Conference on Icing of Aircraft, Engines, and Structures