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040 _aEG-GiCUC
_beng
_cEG-GiCUC
041 0 _aeng
049 _aDeposite
097 _aPh.D
099 _aCai01.13.01.Ph.D.2014.Ah.O
100 0 _aAhmed Mohamed Elsayed Ahmed
245 1 0 _aOptimization of turbine film cooling using navier stokes equations /
_cAhmed Mohamed Elsayed Ahmed ; Supervised Mohamed Madbouli Abdelrahman , Farouk Mohamed Owis
246 1 5 _aالتصميم الأمثل للتبريد الغشائى لتوربينة بإستخدام معادلات نافير ستوكس
260 _aCairo :
_bAhmed Mohamed Elsayed Ahmed ,
_c2014
300 _a137 P. :
_bplans , photographs ;
_c30cm
502 _aThesis (Ph.D.) - Cairo University - Faculty of Engineering - Department of Aerospace Engineering
520 _aOver the past fifty years, aircraft and power generation gas turbine designers have focused on increasing the temperature at the combustor exit to improve the engine performance, to increase the thrust and to reduce the fuel consumption. Unfortunately, these high temperatures have a negative effect on the integrity of the high-pressure turbine components and specifically the turbine blades. Therefore, there is a need to have an efficient cooling system engineered in a way such that the maximum blade surface temperature during the engine operation does not exceed the maximum allowable temperature of the blade material. In addition, the tip leakage flow across the turbine blade reduces its aerodynamic performance and causes blade - tip overheating due to this high speed flow and the existence of a thin boundary layer. Film cooling is vital to gas turbine blades to protect them from high temperatures and hence high thermal stresses. In the current study, film cooling on a flat plate is studied numerically to select the different parameters of the compound - hole shape that could enhance the cooling effectiveness
530 _aIssued also as CD
653 4 _aBlade
653 4 _aCooling
653 4 _aOptimizations
700 0 _aFarouk Mohamed Owis ,
_eSupervisor
700 0 _aMohamed Madbouli Abdelrahman ,
_eSupervisor
856 _uhttp://172.23.153.220/th.pdf
905 _aNazla
_eRevisor
905 _aSamia
_eCataloger
942 _2ddc
_cTH
999 _c50930
_d50930