| 000 | 01879cam a2200325 a 4500 | ||
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| 003 | EG-GiCUC | ||
| 008 | 160119s2015 ua hd f m 000 0 eng d | ||
| 040 |
_aEG-GiCUC _beng _cEG-GiCUC |
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| 041 | 0 | _aeng | |
| 049 | _aDeposite | ||
| 097 | _aM.Sc | ||
| 099 | _aCai01.13.11.M.Sc.2015.Mo.C | ||
| 100 | 0 | _aMohamed Samir Mohamed | |
| 245 | 1 | 0 |
_aCFD simulation for the film cooling of gas turbine blades / _cMohamed Samir Mohamed ; Supervised Essam E. Khalil , Hatem O. Haridy , Esmail M. Elbialy |
| 246 | 1 | 5 | _aدراسة عددية لنمذجة التبريد الغشائى من خلال الممرات لريش التوربينات الغازية |
| 260 |
_aCairo : _bMohamed Samir Mohamed , _c2015 |
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| 300 |
_a67 P. : _bcharts , facsimiles ; _c30cm |
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| 502 | _aThesis (M.Sc.) - Cairo University - Faculty of Engineering- Department of Mechanical Power Engineering | ||
| 520 | _aThis research aims to study and analyze the heat transfer of fluid throughturbine blades. Internal cooling blades technique has been used to cool the gas turbine blades .Gas turbine blade cooling is used to save and protect the gas turbine from catastrophic failure due to high thermal stresses. 1, 550,000 of cells have been used to solve that problem. CFD has been used to evaluate the effect of cooling fluid flow rates into the blades on the flow coefficient. An optimization study using ANSYS has been studied to show the effect of the distance between holes and the best flow inlet angle for the cooling fluid through turbine blade | ||
| 530 | _aIssued also as CD | ||
| 653 | 4 | _aCooling | |
| 653 | 4 | _aFilm cooling | |
| 653 | 4 | _aGas turbine | |
| 700 | 0 |
_aEsmail Mohamed Aly Elbialy , _eSupervisor |
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| 700 | 0 |
_aEssam E. Khalil , _eSupervisor |
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| 700 | 0 |
_aHatem Omar Haridy , _eSupervisor |
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| 905 |
_aAml _eCataloger |
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| 905 |
_aNazla _eRevisor |
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| 942 |
_2ddc _cTH |
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| 999 |
_c54601 _d54601 |
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