| 1. | Numerical simulation of leading edge film - cooling of turbine stator blades
气膜冷却涡轮导向叶片流场数值模拟 |
| 2. | Numerical simulation of film - cooling in turbine cascade with two rows of staggered coolant holes
涡轮叶栅双排孔气膜冷却数值模拟 |
| 3. | The aerodynamic losses and the coolant consumption due to endwall film - cooling are quantified , thus providing data on both the aerodynamic costs and the cooling benefits of endwall film - cooling
这种气动力损失和冷却空气损耗的定量化，可为端壁气膜冷却技术的气动力成本和冷却效益提供数据。 |
| 4. | Understanding the three - dimensional nature of these flows and understanding the interactions between the ejected coolant and the endwall flow are the key to a successful endwall film - cooling design . results from this investigation enhance this understanding
揭示流场的三维特性以及喷射的冷空气与端壁附近的外流场相互作用规律是涡轮叶栅端壁气膜冷却设计成功的关键，本文的研究成果增加了对此规律的更深入了解。 |
| 5. | These measurements are complemented by measurements of the flow field downstream of the cascade . the integrated losses and locations of secondary flow features with and without endwall film - cooling are determined for variations of both coolant supply pressure and injection location
以无端壁气膜冷却和有端壁气膜冷却两种情况进行研究，对比地获得了两者的综合损耗和二次流特征区域随冷却气体供给压力和注射位置的变化规律。 |
| 6. | One cooling method that has gained increasing importance is endwall film - cooling , where coolant air is discharged though discrete holes in the inner and outer endwalls of a turbine blade passage . after leaving the holes , the coolant forms a protective layer between the hot mainstream gas and the surface that is to be protected
目前广泛采用的一种重要冷却方法是涡轮叶栅端壁气膜冷却，该方法中冷空气穿过涡轮叶片上内外端壁离散冷却孔进行交换，且冷空气流经冷却孔后在主流热空气与被保护表面之间形成保护层。 |
| 7. | The distribution of adiabatic film - cooling effectiveness on the endwall of this cascade has been measured using a new technique that has been developed as part of this project . using this new technique , the achieved levels of cooling effectiveness are quantified and over , and under - cooled regions on the endwall are identified
在发展一种新的测试技术的基础上，结合叶栅下游流场测量，获得了叶栅端壁上冷却膜隔热效率的分布，使得叶栅端壁上下冷却层的冷却效率可分别定量描述。 |
