| 1. | Influences of swept and curved blade on the flow near compressor cascade endwall
掠对压气机端壁流动的影响 |
| 2. | Application of endwall boundary layer suction in the stator cascade of steam turbine governing stage
端壁边界层抽吸技术在汽轮机调节级静叶栅中的应用 |
| 3. | Both numerical and experimental investigations were carried out to study the effect of aerodynamic sweeping - curving on the endwall flow field of compressor cascade
摘要利用数值和实验方法对气动弯掠在压气机叶栅中的作用机理进行了研究。 |
| 4. | 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。 |
| 5. | The ejected coolant interacts with the external flow near the endwall and generates aerodynamic and thermodynamic losses in the process . this reduces turbine stage efficiency and together with the consumption of cooling air is detrimental to the overall cycle efficiency
但这种方法中喷射的冷空气与端壁附近的外流场相互作用产生气动力和热动力损失，并且消耗冷却空气，从而损害涡轮的整体循环效率。 |
| 6. | 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。 |
| 7. | 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。 |
| 8. | 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。 |
| 9. | Based on an engineering background , through numerical simulation of the flow field in the hp turbine of the energy efficient engine ( e3 ) , the article research the unsteady flow in a transonic turbine stage , the unsteady phenomena in the stage include the shockwave , wake , shedding vortex , endwall vortex , passage vortex and leakage vortex , etc . there are two shockwaves generated on the vane the tailing edge , one on suction side is named moving shockwave , and name another on pressure side steady shockwave
本文首先对于研究的意义和国内外研究的现状做了简要的介绍，再从某工程背景出发，通过对e3发动机高压涡轮内流场的数值模拟，研究了干涉的周期性的问题，以及涡轮级内常见的非定常现象：激波、尾迹、脱落涡、根脚涡、通道涡、漏流涡。导向器尾缘会出现两道激波，在吸力面的激波可称为“运动”激波，压力面的激波可称为“定常”激波。 |
| 10. | The vortex simulated in this article include the shedding vortex induced by the vane trailing edge boundary layer , the endwall vortex generated by the endwall boundary layer interaction , the passage vortex generated by the rotor rotation , and the leakage vortex generated by the tip clearance flow
涡轮级内的涡运动包括：导向器叶片尾缘附而层引起的脱落涡；转子通道内转子的旋转运动产生的通道涡；根脚区两个端壁附面层干涉，形成的根脚涡；存在叶尖漏流时，出现的漏流涡。 |
