| タイトル | Leading edge film cooling effects on turbine blade heat transfer |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950022694 |
| 著者（英） | Gaugler, Raymond E.; Garg, Vijay K. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1995-06-01 |
| 言語 | eng |
| 内容記述 | An existing three dimensional Navier-Stokes code, modified to include film cooling considerations, has been used to study the effect of spanwise pitch of shower-head holes and coolant to mainstream mass flow ratio on the adiabatic effectiveness and heat transfer coefficient on a film-cooled turbine vane. The mainstream is akin to that under real engine conditions with stagnation temperature = 1900 K and stagnation pressure = 3 MPa. It is found that with the coolant to mainstream mass flow ratio fixed, reducing P, the spanwise pitch for shower-head holes, from 7.5 d to 3.0 d, where d is the hole diameter, increases the average effectiveness considerably over the blade surface. However, when P/d= 7.5, increasing the coolant mass flow increases the effectiveness on the pressure surface but reduces it on the suction surface due to coolant jet lift-off. For P/d = 4.5 or 3.0, such an anomaly does not occur within the range of coolant to mainstream mass flow ratios analyzed. In all cases, adiabatic effectiveness and heat transfer coefficient are highly three-dimensional. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 95N29115
NASA-TM-106955
E-9705
NAS 1.15:106955 |
| 権利 | No Copyright |
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