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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.3 pt.A; 20050606-09; Reno-Tahoe,NV(US) >LOCAL INTERNAL IMPINGEMENT HEAT TRANSFER NEAR A 30 AND 90 DEG ROW OF FILM COOLING HOLES: PART 1-EFFECT OF FLOW PARAMETERS
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LOCAL INTERNAL IMPINGEMENT HEAT TRANSFER NEAR A 30 AND 90 DEG ROW OF FILM COOLING HOLES: PART 1-EFFECT OF FLOW PARAMETERS

机译：膜孔的30和90行附近的局部内部碰撞传热：第1部分流动参数的影响

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Experimental investigations of local impingement heat transfer characteristics near a row of film cooling holes in a simulated internal midchord region of gas turbine blade have been carried out. The research of heat transfer characteristics is focused on three film cooling hole diameter area located upstream and downstream a row of film holes. There is a line of equally spaced film cooling holes whose angles are 30 or 90 degrees. When there is no impingement, the investigation about the effect of the film cooling bleed has been carried out under different cross flow Reynolds Numbers and film outflow-to-crossflow mass flux ratios based on each film cooling hole/channel section area. The results indicate that the local heat transfer near the film cooling holes is enhanced with the increase of the crossflow Reynolds Numbers and film outflow-to-crossflow mass flux ratios based on each film cooling hole/channel-section area. The local heat transfer characteristic downstream film cooling holes is better than that upstream film cooling holes. The average Nusselt number of one time diameter area downstream the row of film holes is generally 40% more than that upstream the row of film cooling holes. The place closer to the hole will have stronger heat transfer whether upstream film cooling holes or downstream film cooling holes. When there is impingement, the impinging air is provided by a single line of equally spaced jets. The spacing of the jet holes is twice that of the film cooling holes with staggered arrangements. The local heat transfer near the row of film cooling holes has been studied experimentally through changing flow parameters, such as impinging Reynolds Numbers and mass flux ratios of crossflow-to-jet based on each channel/jet hole section area etc. A great number of experimental data has been obtained. Based on this, the effects of the flow parameters on the heat transfer characteristics have been obtained qualitatively and quantitatively. It can be the important reference for accurately designing gas turbine blade.
机译：在燃气轮机叶片的模拟内部中弦区域中的一排薄膜冷却孔附近进行了局部冲击传热特性的实验研究。传热特性的研究集中于位于一排薄膜孔的上游和下游的三个薄膜冷却孔直径区域。有一排等距的薄膜冷却孔，其角度为30或90度。在没有碰撞的情况下，已经根据每个薄膜冷却孔/通道截面面积，在不同的错流雷诺数和薄膜出流与错流质量通量比的情况下，对薄膜冷却渗出的效果进行了研究。结果表明，基于每个膜冷却孔/通道截面面积，随着横流雷诺数和膜出流与横流质量通量比的增加，膜冷却孔附近的局部传热得到增强。下游膜冷却孔的局部传热特性优于上游膜冷却孔的局部传热特性。一排膜孔下游的一倍直径区域的平均努塞尔数通常比一排膜冷却孔上游的平均努塞尔数大40％。无论上游膜冷却孔还是下游膜冷却孔，更靠近孔的位置都将具有更强的热传递。当有撞击时，撞击空气是由等距间隔的单行喷射流提供的。喷射孔的间距是交错布置的薄膜冷却孔的间距的两倍。通过改变流动参数（例如，基于每个通道/喷孔截面面积的冲击雷诺数和横流与射流的质量通量比），通过实验研究了成排的薄膜冷却孔附近的局部传热。已获得实验数据。基于此，定性和定量地获得了流动参数对传热特性的影响。为准确设计燃气轮机叶片提供重要参考。

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