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المؤلفShahina, Ibrahim
المؤلفAlqaradawi, Mohamed
المؤلفGadala, Mohamed
المؤلفBadr, Osama
تاريخ الإتاحة2021-09-07T06:16:21Z
تاريخ النشر2016
اسم المنشورJournal of Engineering and Applied Sciences
المصدرScopus
الرقم المعياري الدولي للكتاب1816949X
معرّف المصادر الموحدhttp://dx.doi.org/10.3923/jeasci.2016.2769.2774
معرّف المصادر الموحدhttp://hdl.handle.net/10576/22824
الملخصThe 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. Medwell Journals, 2016.
راعي المشروعThs publication was made possible by NPRP grant No. 4-651-2-242 from the Qatar National Research Fund (a member of Qatar Foundation). The statements made herein are solely the responsibility of the researchers.
اللغةen
الناشرMedwell Journals
الموضوعBlade tip
Centrifugal compressor
Losses
Performance and stability
Surge
العنوانEffect of blade tip geometry on centrifugal compressor performance and stability
النوعArticle
الصفحات2769-2774
رقم العدد12
رقم المجلد11
dc.accessType Abstract Only


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