Endwall geometric uncertainty and error on the performance of TUDA-GLR-OpenStage transonic axial compressor
نویسندگان
چکیده
The hub and casing walls of axial compressors are often modeled as smooth continuous surfaces in CFD simulations, but real geometries, non-smooth pinches, steps leakage cavities may exist. In the GPPS first Turbomachinery Workshop, a comprehensive validation verification campaign RANS flow solvers was conducted, all simulation results consistently over-predicted total pressure ratio at rotor exit near stator hub. From recent examination test rig geometry, pinched wall over cavity below were found, which not considered workshop. this paper, effects these endwall geometric uncertainties errors analyzed via numerical simulation. When considering pinch predicted choke mass compressor stage smaller than that without pinch, leading to better agreement with measured data. rate about 0.2% inlet flow, near-hub distribution matches slightly experimental data, on global characteristics visible. relevant mechanisms changes performances detail. updated geometries grids will be released public benchmark case for turbomachinery verification.
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ژورنال
عنوان ژورنال: Journal of the Global Power and Propulsion Society
سال: 2023
ISSN: ['2515-3080']
DOI: https://doi.org/10.33737/jgpps/161708