| 1. | Combined features of the inner impingement and outer film cooling holes of a vane
内部冲击和外部气膜的组合特性研究 |
| 2. | Experimental investigation of discharge coefficients of film cooling hole on turbine blade
吹风比对涡轮动叶型面气膜孔流量系数的影响 |
| 3. | The performance of flat surface film cooling with 30 film cooling holes along streamwise was experimentally investigated using thermal liquid crystal
摘要采用热色液晶测温法，对沿流向倾角30的圆孔排平板气膜冷却进行了实验研究。 |
| 4. | Numerical investigation for local heat transfer characteristics of the inner side of turbine blade near film cooling holes , whether there is impingement or no has been carried out with an rsm turbulence model
摘要用rsm模型对有、无冲击气膜出流冷气侧气膜孔局部换热特性进行了数值研究。 |
| 5. | In order to study the influence of dimensional configuration of the film cooling hole on the discharge coefficient , some kinds of film cooling holes with different dimensional configuration were designed
摘要为了研究火焰筒壁面气膜冷却孔几何结构对流量系数的影响规律，设计了几种具有不同几何尺寸和排列结构的气膜冷却孔实验件。 |
| 6. | When there is no impingement , the investigation about flow extravasation effect form film cooling holes is carried out with different cross flow reynolds numbers and different density flow ratios of the film outflow to cross flow
在无冲击射流时，通过改变来流雷诺数、气膜出流与横流密流比，对气膜孔的“溢流效应”进行了研究。 |
| 7. | When there is impingement , the effect of flow and geometrical parameters on the local heat transfer characteristics near film cooling holes is investigated , and the mechanism of local heat transfer characteristics is obtained
在有冲击射流时，着重研究了流动和几何参数对气膜孔局部换热特性的影响，分析了“冲击气膜出流”局部换热特性规律。 |
| 8. | The results showed that the discharge coefficient of film cooling hole was greatly increased with the increase of blow ratio when the blow ratio m is lower , buta it had a little increase with the increase of m when m is larger
实验结果表明，在吹风比较小时，随吹风比的增加流量系数大幅度增加，当吹风比较大时，随吹风比的增加流量系数增幅减小。 |
| 9. | The method of prediction the discharge coefficients of film cooling holes on the turbine blade suggested by d . a . rowbury et . al has been improved in this paper to fit the computations in the cases of low pressure ratios and the holes in leading edge region especially . the effects of external cross - flow , hole geometry and reynolds number in the hole were taken into account . an additive loss coefficient method is subsequently applied to the test data in order to assess the effect of the external cross - flow
Rowbury等提出的流量系数工程算法进行了改进，计算结果和实验数据的比较表明改进后的新模型使低吹风比和前缘驻点附近流量系数的计算得到了明显的改进，而在高吹风比下仍能保持与实验数据相符，这种算法有可能成为低压比情况下型面气膜冷却的一种通用设计方法。 |
| 10. | Above all , the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream reynolds number of 150000 , 200000 50000 , 300000 , 350000 , 400000 . then , the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly . and it ' s studied how the mainstream reynolds number , blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade
对导叶和动叶，都是先研究了在150000 ， 200000 ， 250000 ， 300000 ， 350000 ， 400000雷诺数下，没有气膜冷却时的表面换热系数分布，然后研究了气膜孔全打开和只打开单排孔时的表面换热系数分布曲线，重点研究来流雷诺数，吹风比和不同孔位出流对换热系数分布的影响规律。 |
