為了提高渦輪引擎燃油使用效率與輸出功率，工程上普遍透過提高渦輪進口溫度來達到這個目標，然而也因燃氣溫度遠高於渦輪葉片所能承受的範圍，因此需要導引壓縮機的低溫氣流來冷卻以保護葉片。本研究的目的是利用數值方法來模擬分析含薄膜冷卻渦輪靜子葉片的熱傳，並探討冷卻氣流量與壁面熱傳的關係。使用的數值計算工具為CFX-TASCflow軟體，為了驗證數值計算工具的準確度，研究中首先針對二維含肋條管道、旋轉中的方型管與無薄膜冷卻渦輪靜子葉片的熱傳現象進行計算分析，並與相關實驗數據比較後得到不錯的結果。在旋轉方形管熱傳模擬中，為了減少因原模型方型轉角造成流體急速轉彎分離而形成的壓力損失，將方管轉角改成圓弧型來模擬其流場。雖然圓弧型轉角成功地減少方形管內的壓力損失，但轉角處與第二個通道中的壁面熱傳卻也因此有了些許的下降。

在含薄膜冷卻渦輪葉片熱傳模擬研究中，為了準確模擬壁面熱傳分布，紊流的計算採用SST紊流模型，計算區域則包含葉片流道、冷卻噴孔與氣室。計算模型為一渦輪靜子葉片，並在吸力面上鑽有兩排相鄰交錯的圓錐形噴孔。模擬結果發現吹出比m=0.45時的壁面平均熱傳係數分布趨勢與實驗相符，然而在吹出比m=0.6與m=1.0時噴孔附近的熱傳分布則有較大的差異，即使在遠離噴孔處有較接近的結果，在吹出比m=1.0時噴孔附近的熱傳結果甚至比實驗值高。在高吹出比下數值結果與實驗值的差異應來自於熱傳模擬中冷卻氣流已抬升遠離壁面，但在實驗中並無此現象的結果。實驗中此冷卻氣流抬升的現象可能在吹出比大於1.0的情況下發生，但在此熱傳模擬相對較低的吹出比範圍內卻提早發生。

為了探討冷卻氣流量與壁面熱傳的關係，本研究熱傳模擬的吹出比範圍為m=0.15-1.0。模擬結果發現吹出比越高，遠離噴孔的平均壁面熱傳係數會越低，這是由於保護葉片不受外界熱氣影響的冷卻氣流量增加的緣故。但在靠近噴孔處，平均壁面熱傳係數則呈現先降低後增加的趨勢。除此之外，在吹出比大於0.45之後平均壁面熱傳係數的分佈會有一峰值與谷值出現。在分析過靠近噴孔處的溫度場分佈後，發現冷卻氣流在噴出之後的下游處形成一對轉渦旋，且渦旋的尺度隨著吹出比的增加而增大。而在m=1.0時帶有高動量的冷卻氣流被噴離了壁面，使得外界熱氣鑽入冷卻氣流的下方來接觸壁面。這代表過高的吹出比會導致氣流抬升現象，使得靠近噴孔處的熱傳增加、冷卻效率下降。這也表示了增加吹出比並不完全是提昇冷卻效率的好方法，選擇一個適當的吹出比來操作可更有效率地冷卻渦輪葉片。另外，因冷卻氣流噴出所形成的對轉渦旋而被捲入的外界熱氣也會導致冷卻效率的下降。由於冷卻氣流的抬升與外界熱氣的捲入會造成在高吹出比時葉片壁面熱傳的增加與冷卻效率的下降，如何找出較佳的冷卻方式來避免這些現象的發生將是未來的研究重點。

Raising the turbine entry temperature is a common method to increase the performance and power output of a gas turbine engine. However, the level of turbine entry temperature is much higher than the blade material can endure. Thus, it is necessary to guard the blade against the entering hot gas by guiding cooling air from the compressor into the turbine. The purpose of this research is to numerically simulate the flowfield and temperature distribution of gas turbine blades with film cooling, and then to investigate the influence of coolant quantity on the blade heat transfer. The finite element based finite volume method CFD software, CFX-TASCflow, was adopted as the numerical tool. To validate the numerical tool, thermal simulations in a 2D channel with symmetric ribs on the walls, a rotating square channel, and a turbine nozzle without film cooling were conducted, and the numerical results were in good agreement with the experimental measurements. In the thermal simulations of a rotating square channel, the models with round corners were also tested to reduce the pressure loss resulting from the separations at the sharp corners in the original model. Though it was successful in decreasing the pressure loss by replacing the sharp corners with the round corners, the wall heat transfer was also reduced at the turn and in the second pass with the modifications.

In order to improve the numerical prediction of heat transfer on a turbine blade with film cooling, the SST turbulence model was adopted to simulate the turbulent flow. The computational domain included the blade passage, the coolant holes, and the plenum. The test model was a turbine nozzle blade and two staggered rows of conical holes drilled on the suction side as the cooling holes. The results indicated that the averaged heat transfer coefficient distribution agreed with the experimental measurements satisfactorily at a blowing ratio of m=0.45. Noticeable discrepancies on are discovered near the rear hole at m=0.6 and m=1.0, even though the results agree with the measured data downstream away from the holes. The average heat transfer coefficient in the region near the holes is even overpredicted at m=1.0. The discrepancies resulted from the lift-off phenomenon which occurred in the heat transfer prediction at high blowing ratios, but not in the heat transfer measurements. It would be discovered at a higher blowing ratio than 1.0, but occurs too early at this relatively low blowing ratio in this computation.

In order to investigate the influence of the blowing ratio on the turbine blade heat transfer, the numerical predictions were performed in the range of a blowing ratio m=0.15-1.0. It was found that with increasing the blowing ratio, the average heat transfer coefficient decreased on the wall downstream away from the holes because the cooling air injected for wall protection from the ambient hot gas was increased. But the average heat transfer coefficient decreased first and then increased in the vicinity of the holes. In addition, a peak and a valley value also appeared in the average heat transfer coefficient distribution as m>0.45. After analyzing the thermal field in the vicinity of the holes, it was discovered that a pair of counter-rotating vortices formed while the cooing air was ejected out of the holes. The scales of the induced vortices became greater as the blowing ratio was increased. At m=1.0, the cooling air with high momentum lifts off the surface, and the ambient hot gas completely flows below the cooling air. This implies that an excess blowing ratio causes wall heat transfer to increase while poor cooling effectiveness near the film cooling holes is due to the lift-off phenomenon. This also means that increasing the blowing ratio is not always a good way to improve cooling at any given position on the suction side. Choosing an adequate blowing ratio can make the cooling air cool the turbine blades more effectively. In addition, the entrainment by the induced counter-rotating vortices also degrades the cooling effectiveness near the film cooling holes. Cooling air lift-off and hot gas entrainment by induced vortices result in high wall heat transfer and poor cooling effectiveness at high blowing ratios. Finding the cooling configuration to prevent cooling air lift-off and hot gas entrainment will be the focus for the future research.

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