共查询到19条相似文献,搜索用时 62 毫秒
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本文采用SST湍流模型模拟了类前缘通道内蒸汽射流阵列冲击冷却的流动与传热特性,分析了雷诺数(Re=10000~50000)、孔径比(d/H=0.5~0.9)和孔间距比(S/H=2~6)对流动及传热性能的影响规律,得到了相应的传热和摩擦关联式。结果表明:在不同雷诺数下,d/H从0.5到0.9变化时,通道压力损失系数降低了76%~79%,靶面平均努塞尔数降低了45%~49%;S/H从2增至6时,通道压力损失系数增加了1.64~1.92倍,靶面平均努塞尔数增加了54%~64%;增大d/H、减小S/H可有效提高类前缘通道蒸汽冲击冷却的综合热力系数。本文研究结果可为未来先进燃气轮机高温涡轮叶片蒸汽冷却结构的设计提供参考和借鉴。 相似文献
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交错肋是航空发动机涡轮叶片的一种高性能内冷结构,为研究涡轮叶片内部交错肋冷却结构的流动和传热特性,针对30?、35?和45?三种肋倾角的交错肋结构进行了雷诺数在17000~70000之间的稳态传热实验和数值模拟研究。数值计算的有效性通过与实验结果进行对比得到充分验证。实验结果显示,在子通道个数和雷诺数均相同的情况下,平均Nu数和摩擦因子均随肋倾角的增大而增加;对比30?倾角的交错肋结构,45?倾角交错肋结构的平均Nu数增加了40.7%,摩擦因子增加了204.9%,综合传热性能提升了13.4%。数值计算结果显示,肋倾角的增大不仅增强了转向区域的冲击作用,而且加强了对侧子通道间的流动掺混,从而达到强化传热的效果。 相似文献
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通过数值模拟的方法,揭示了整级涡轮叶片在旋转状态F的气膜冷却特性.计算采用六面体结构化网格,湍流模型选用k-ε两方程模型.计算中,主流进口雷诺数为7.7×104,旋转数分别为2.092,2.324和2.448,吹风比分别为0.5、1.0、1.5和2.0,冷却工质采用空气,对应射流主流密度比为1.03.计算结果与之前的实... 相似文献
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在掺杂(~3%重量比)碳纳米管和光敏取向基团的向列态液晶薄膜(5μm厚)中,在使用Ar+(514.5nm)为激发光做前向多波混频实验时,观察到7级的自衍射和探测光He-N e(632.8nm )的多级衍射均呈多环状结构.高斯光束中心处的光致非线性折射率系数δn~0.8. Ar+ (514.5nm)连续光形成光栅的时间和弛豫时间都与写入光的偏振态强烈相关.在使用Nd :YAG(532 nm)为激发光时,光栅的弛豫时间~200ms量级,且探测光He-Ne(632.8nm)的o光和e光所探 测到的动力学响应曲线是不同的.
关键词:
瞬态
稳态
多波混频
液晶 相似文献
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高温涡轮叶片三种内冷通道冷却性能的实验研究 总被引:2,自引:0,他引:2
本文用实验方法研究了高温涡轮叶片三种内冷通道的压力分布、冷热态流阻及局部换热系数分布.叶片前部分别采用径向光滑通道、集中冲击冷却和分散冲击冷却三种结构,叶片后部则分别采用三排φ3扰流柱和五排φ2扰流柱稠密布置两种结构.对这三种结构进行了冷却性能比较,提出了该类冷却通道的最佳结构. 相似文献
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带气膜孔内部冷却通道的流动传热特性 总被引:2,自引:0,他引:2
燃气轮机高温透平内部冷却通道中弯头、肋片和气膜孔之间存在着复杂的交互作用。本文采用瞬态液晶技术对光滑通道、无抽吸的带肋通道和有气膜孔抽吸的带肋通道的表面传热分布和沿程压力损失进行了详细测量,同时采用RANS数值模拟方法研究其流场特性。结果表明180°弯头产生的大分离是压力损失的主要因素,45°斜肋片产生的螺旋形流动在弯头与大分离交互作用明显,气膜孔抽吸破坏孔附近边界层使得肋间传热而相对集中于孔附近。在13%抽吸量条件下,气膜孔抽吸降低U型通道中压力损失约20%,同时保持传热强化程度与无抽吸工况相同。 相似文献
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涡轮叶顶冷却布置对叶顶传热冷却性能的影响 总被引:2,自引:0,他引:2
本文采用数值模拟的方法,对比分析了1+1/2对转涡轮四种不同的叶顶冷却布置方案对叶顶传热、冷却性能以及气动特性的影响。四种布置方案分别是:靠近压力面垂直叶顶方向、靠近压力面且与叶顶有30°出射角、中弧线位置垂直叶顶方向、中弧线位置有30°出射角。研究表明,气膜孔沿压力面布置与气膜孔沿中弧线布置相比可以降低叶顶传热系数;由于气膜孔倾斜布置气膜射流动量降低,且削弱了肾形涡的影响,气膜的侧向覆盖范围增大。因此气膜孔靠近压力面布置可以提高气膜冷却效率;气膜孔靠近压力面且有30°出射角比垂直布置叶顶热负荷减少2.7%。另外,气膜孔靠近压力面布置可以降低主流的泄漏流量,有利于减小泄漏损失和提高涡轮效率。 相似文献
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Transient heat transfer of liquid methane under forced convection in a 1.8 mm × 1.8 mm asymmetrically heated square channel was investigated. This study is aimed at understanding the heat transfer behavior of cryogenic propellant in cooling channels of a regeneratively cooled rocket engine at the start-up condition. To simulate high heat load conditions representative of regeneratively cooled rocket engines, a high heat flux test facility with cryogenic liquid handing capabilities was developed at the Center for Space Exploration Technology Research. The time history of inlet and outlet fluid temperatures and test section channel wall temperatures were measured at high heat flux conditions (from 1.19 to 3.80 MW/m2) and a Reynolds number (Re) range of 1.88 × 105 to 3.45 × 105. The measured wall temperature data point toward possible film boiling within the test section during certain tests, particularly with higher heat fluxes and lower Reynolds number conditions that resulted in higher wall temperatures. The transient average Nusselt numbers (NuL) of the channel obtained from the experimental measurements are lower than those calculated from the Sieder–Tate correlation (NuO); however, the ratio (NuL/NuO) increases with the increase in Reynolds number. The ratio is around 0.25 at the lower end of Re and then increases to 0.7 at the maximum Re studied in the present investigation. 相似文献
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Experiments on triangular and rectangular array jet impingement and single-phase spray cooling have been performed to determine the effect of both cooling techniques on heat transfer coefficient (h) and the coolant mass flux required for a given cooling load. Experiments were performed with circular orifices and nozzles for different H/D values from 1.5 to 26 and Reynolds number range of 219 to 837, which is quite lower than the ranges employed in widely used correlations. The coolant used was polyalphaolefin. The experiments simulated the boundary condition produced at the surface of the stator of a high power low-density generator or motor. For the custom fabricated orifices, commercial nozzles, and conditions used in this study, both cooling configurations showed enhancement of heat transfer coefficient as H/D increases to a certain limit after which it starts to decrease. The heat transfer coefficient always increases with Reynolds number. In keeping with previous studies, single-phase spray cooling technique can provide the same heat transfer coefficient as jets at a slightly lower mass flux, but with much higher-pressure head. Special Nud correlations that account for the range of parameters and coolant studied in this work are derived. 相似文献
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Liquid crystal thermography was used in a water-operated concentric tube-in-tube heat exchanger to determine local annular heat transfer coefficients at the inlet region. An annular diameter ratio of 0.54 was considered with the inlet and outlet orientated perpendicularly to the axial flow direction. Both heated and cooled cases were considered at annular Reynolds numbers ranging from 1,000 to 13,800. Wall temperature distributions were directly measured by means of a coating of thermo-chromic liquid crystals. Local heat transfer coefficients at the inlet were higher than those predicted by most correlations, but good agreement was obtained with some literature. 相似文献
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燃烧室出口辐射对气膜冷却传热影响研究 总被引:2,自引:0,他引:2
燃气轮机高温透平中包含对流/导热/辐射等复杂传热现象。本文依托高温流热固耦合实验台,提出燃烧室与透平联合计算的方法,采用数值模拟和实验对比的方式分析了平板气膜冷却的对流/导热/辐射传热特性。同时研究了不同燃气吸收系数以及不同进口辐射条件对于平板气膜冷却的表面温度分布的影响。结果表明:辐射传热是燃气轮机首级高温叶片传热特性的重要影响因素,辐射传热使得实验平板温度抬升50~70 K,燃烧室/透平联合计算方法有效地分析了燃烧室出口辐射强度对高温平板气膜冷却辐射传热的影响;高温燃气辐射特性对于平板温度分布具有明显影响。 相似文献