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This paper describes an experimental study on film cooling effectiveness of circular and fan-shaped film cooling holes with a swirling film coolant injected through the endwall of a high-loaded 1st nozzle. The experiments have been conducted by using a two dimensional vane cascade, designed based on the firststage vane of E (Energy Efficient Engine) engine studied by a NASA project. The film cooling effectiveness on the endwall of the enlarged 1st nozzle of E turbine was measured by using pressure sensitive paint (PSP) techniques. It appeared from the experimental results that the film cooling effectiveness of a circular hole was improved by increasing the angle of two impingement jets inside the cavity, which is used both to cool internal wall and to produce a swirling motion of film coolant. On the other hand, it was found that there exists an optimal jet angle between  to 15 degrees in the case of a fan shaped film cooling hole. Thus the new film cooling method with swirling cooling air has been demonstrated to maintain its high film cooling effectiveness even under such a complicated flow field.

An experimental study of a film cooling with swirling flow on the endwall of a high loaded 1st nozzle