@article{MAKHILLJEAS2016111213972,
    title = {Effect of Blade Tip Geometry on Centrifugal Compressor Performance and Stability},
    journal = {Journal of Engineering and Applied Sciences},
    volume = {11},
    number = {12},
    pages = {2769-2774},
    year = {2016},
    issn = {1816-949x},
    doi = {jeasci.2016.2769.2774},
    url = {https://makhillpublications.co/view-article.php?issn=1816-949x&doi=jeasci.2016.2769.2774},
    author = {Ibrahim},
    keywords = {performance and stability,centrifugal compressor,surge,losses,Blade tip},
    abstract = {The reliability operation for small fuel cells and hybrid fuel cell with gas turbine requires centrifugal
compressor surge prevention. This study concerns a high speed centrifugal compressor stage with different
blade tip geometries. The investigations were performed with unsteady three-dimensional, compressible flow
simulations. A novel parameterization method has been developed to alter the tip geometry of an impeller blade.
Different tip geometries are investigated includes flat tip blade, main blade winglet, main and splitter blade
winglet and finally pressure side grooved tip. The performance and internal flow results are presented at surge,
design and near choke points. The conclusion is that the tip geometry has a significant effect on the
compressor performance and the operation stability at lower flow rates. The pressure ratio and surge margin
for the blades with winglet have been improved and decreased for the grooved tip geometry. More uniform flow
at impeller outlet with winglet blade. The use of winglet tip displaces the tip leakage vortex away from the blade
and weakening the impingement effect. The winglet tip reduce the aerodynamic losses by unloading the tip
section, reducing the leakage flow rate and turning the leakage flow in a more stream wise direction.}
    }