الفهرس 
Chapter (1) IntroductionOnly 14 pages are availabe for public view
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Abstract
Film cooling effectiveness of the turbine blade suction side under different operating conditions: Reynolds numbers, pressure ratios, and blade rotation speed is numerically investigated. At the blade suction side, five film holes row locations from the blade leading edge at 3%, 7%, 10%, 31%, and 69% of the axial chord length were investigated. Coolant is injected from eleven cylindrical holes at blowing ratios ranged from 0.91 to 2 and rotational speeds ranged from 0 to 4600 rpm. The investigation is performed at five Reynolds numbers of the mainstream hot gases. The inlet temperature of the hot gases is 1500 K, while the coolant inlet temperature is 650 K for all the investigated cases. Effects of coolant injection to mainstream pressure ratio varied in the range from 1.18 to 1.53 are studied. Location 2 (7% from blade leading edge) showed the highest film cooling effectiveness. Near the film holes, the increase in film cooling effectiveness of location 2 is by 37% than location 1(3% from blade leading edge), 13% than location 3(10% from blade leading edge), 44% than location 4 (31% from blade leading edge) and 73% than location 5 (69% from blade leading edge). For all locations as the blowing ratio increases the film cooling effectiveness increases. The film cooling effectiveness increases as the rotation speed increases until reaches its optimum value and then decreases. Also, as the coolant pressure ratio increases, the film cooling effectiveness slightly enhances till it has an optimum value at a coolant pressure ratio of 1.45. Due to the increase in turbine inlet temperature as the result of blade film cooling, the efficiency and power of the ideal cycle for gas turbine engine increase by 2.5 % and 34 %, respectively.