کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
662587 | 1458179 | 2005 | 15 صفحه PDF | دانلود رایگان |
![عکس صفحه اول مقاله: Heat transfer and film-cooling for the endwall of a first stage turbine vane Heat transfer and film-cooling for the endwall of a first stage turbine vane](/preview/png/662587.png)
Secondary flows that result in turbomachines from inherent pressure gradients in airfoil passages, are the main contributors to aerodynamic losses and high heat transfer to the airfoil endwalls. The endwalls present a challenge to durability engineers in maintaining the integrity of the airfoils. One means of preventing degradation in the turbine is to film-cool components whereby coolant is extracted from the compressor and injected through small cooling holes in the airfoil surfaces. In addition to film-cooling, leakage flows from component interfaces, such as the combustor and turbine, can provide cooling in localized areas but also provide a change to the inlet boundary condition to the passage. This paper presents measurements relevant to the endwall region of a vane, which indicate the importance of considering the inlet flow condition.
Journal: International Journal of Heat and Mass Transfer - Volume 48, Issues 25–26, December 2005, Pages 5255–5269