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To maximize the turbine thermal efficiency, modern gas turbine's inlet temperature is significantly augmented within the past few decades. To prolong the lifespan of gas turbines, many efficient cooling techniques have been proposed and applied in the endwall cooling schemes. However, conventional discrete film hole does not take effect at the leading edge nearby region. In this research, how the trenched film hole configurations affects the endwall cooling and phantom cooling characteristics were deeply studied by using a verified approach. Steady 3D Reynolds-averaged Navier-Stokes(RANS) governing equations together with the shear stress transport(SST) k-w turbulence model have been solved. Firstly, results indicate that trenched film holes greatly influence the cooling effectiveness at leading edge nearby region compared to normal case. Nevertheless, suction side phantom cooling is hardly influenced by the trenched film holes. Secondly, the case with a smaller trench width obtains higher endwall cooling effectiveness, particularly at upstream region. More importantly, the cases with W=3D achieve large cooling effectiveness at leading edge nearby region with little influence by trench depth. Additionally, majority of trenched film holes coolant flow is driven towards middle passage. Therefore, the suction side phantom cooling is unaffected by the trenched film holes. 相似文献
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With the booming performances of the gas turbine engine, the turbine vane of the gas turbine engine experiences more extreme thermal environment with supersonic flows. The film cooling applied in the supersonic flow condition has essential difference from that used in the subsonic flow condition in the flow characteristics and cooling effectiveness. This article focused on the film cooling of two parallel flows (primary flow and coolant flow) with supersonic or subsonic velocity, respectively. The results show that: on the condition of supersonic primary flow and subsonic coolant flow, the coolant flow with lower momentum is sheared and dragged by the higher momentum primary flow because of the viscous property of fluid. At the meantime, the thermal and momentum of the primary flow transfers into the coolant flow rapidly. It causes the great damage of the film coverage, and the decrease of the cooling effectiveness dramatically. In contrast, on the condition of supersonic primary flow and supersonic coolant flow, the film coverage of the supersonic coolant flow can last further far than that of the subsonic coolant flow on the same blowing ratio. The turbulence kinetic energy seems to be depressed by the shorten of velocity difference of two supersonic flow. Therefore, the cooling effectiveness is enhanced by 45% for the supersonic primary and coolant flow. 相似文献
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燃气轮机高温叶片气膜冷却系统的研究进展 总被引:3,自引:0,他引:3
气膜冷却是现代燃气轮机透平高温叶片冷却的重要方式。真实透平中的复杂工况对气膜冷却系统提出了严峻的挑战,优化设计气膜冷却系统,提高其冷却性能,同时适应真实透平的工作条件已成为业界关注的一个主要问题。本文综述了近年来在气膜冷却结构设计、气膜冷却系统制造和其在燃机真实条件下运行性能三方面的研究成果。在此基础上提出了气膜冷却研究的发展方向。高温叶片的气膜冷却系统将在更加接近燃机真实运行工况的雷诺数、马赫数、湍流度、吹风比、动量比、密度比以及非稳定流场条件下,沿着优化气膜孔的组合排布、孔形和孔影响区域这三方面进行优化设计,同时考虑加工工艺和长期运行均会导致实际的气膜冷却孔会偏离设计构造的影响。 相似文献
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运用数值模拟的手段,从流动特性和冷却特性两方面评价了各种开槽气膜冷却孔结构的优劣。从流动的机理揭示了在相同的槽深下,不同的横槽结构对改善气膜冷却效率和流量系数的影响,并比较了在气膜孔出口和入口均开有横槽后对流动和冷却特性的影响。结果表明:开横槽后,气膜孔出口下游的冷却效率得到不同程度的改善,吹风比越大,改善的程度越明显。在横槽下游5D-10D的范围内,冷却效率的改善程度最大;在气膜孔出入口处均开有斜横槽的结构和用圆角过渡气膜孔入口处的横槽均是提高气膜冷却效率和减小气膜孔流动阻力的有效措施,而在气膜孔出口处的横槽用圆角过渡则不利于改善气膜冷却效果。 相似文献
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This paper presents three-dimensional numerical simulations with the established realizable k-ε model to clarify the underlying and interacting mechanisms between the film cooling and the internal cooling. On the one hand, the effects of three different internal cooling channels, i.e., smooth channel, continuous ribbed channel, and truncated ribbed channel, on the film cooling effectiveness and the discharge coefficients are investigated. On the other hand, the influences of three different film... 相似文献
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采用存在源项的叶栅三维黏性流数值方法计算与分析了存在气膜射流的燃气侧的流动与换热特性,确定了吹气比、来流湍流度、气膜孔展向间距与展向射流角等因素对气膜有效度的影响,并分析了其机理. 相似文献
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基于控制容积法对三维定常不可压缩N-S方程进行离散,采用分区域非结构化网格及两层k-ε湍流模型,在吹风比M=0.6~1.5的情况下,对新型缩放槽缝形气膜孔进行了详细的平板气膜冷却数值汁算,得到了在喷孔射流下游处及叶高方向上的气膜冷却效率,并研究了其孔长与孔径比L/D对冷却效率的影响.计算结果表明:高吹风比对缩放槽缝孔沿中心线冷却效率的影响较为复杂;缩放槽缝形气膜孔下游的冷却效率并不随吹风比的变化而单调变化,而是在吹风比为1.0时存在最佳值;在孔口下游较远区域,两个相邻孔之间沿叶高方向的气膜覆盖性较好;缩放槽缝孔的冷却效率随着其孔长与孔径比L/D的增大而增大,当L/D>8时,增加的幅度趋缓. 相似文献
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振动平板气膜冷却的数值分析 总被引:1,自引:0,他引:1
《动力工程学报》2015,(9):722-727
采用数值方法模拟振动平板单孔气膜冷却过程,对比不同振动频率、不同振幅和不同吹风比下气膜孔中心线下游绝热壁面的有效温比曲线,并分析了气膜孔周围壁面相对静压分布.结果表明:振动会削弱气膜冷却效果;在吹风比λ=1.0下,不同振幅、不同振动频率振动时绝热壁面的有效温比比稳态时小,且在x/D10时,2种情况下有效温比的差距更明显;同一振动下,在吹风比小于0.6,x/D5振动时绝热壁面的有效温比比稳态时大,在x/D5振动时的有效温比比稳态时小;在吹风比大于0.6振动时的有效温比始终比稳态时小;振动时气膜孔周围壁面相对静压会出现周期性变化. 相似文献
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利用四面体斜坡抑制圆孔下游的CVP(反向旋转涡对),采用PLIF(平面激光诱导荧光)技术,在吹风比为0.5、1.0、1.5和2.0的情况下,针对四面体斜坡与圆形气膜孔的6种相对布置方式,实验研究并分析设置四面体斜坡后对气膜孔下游气膜冷却特性产生的影响。实验研究表明:相对于气膜孔,6种四面体斜坡模型都可以抑制CVP,提高气膜冷却效率;在6种四面体斜坡模型中,气膜孔上、下游同时放置逆风斜坡的组合模型可以取得最长的气膜长度和最高展向平均效率,当吹风比为0.5和2.0时,气膜孔出口下游x/d=3面上的展向平均效率分别是未设置四面体斜坡时的3.7和4.9倍。 相似文献
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为充分利用炼油装置低品位热源,2008年5月,洛阳石化新建两套低温热水系统,Ⅰ套供生产装置工艺使用,替代低压蒸汽;Ⅱ套供生活区和办公区,用做生活热水和冬季采暖。其中,Ⅱ套低温热水系统夏季尚有350t/h的热水富余,需要用循环水冷却至70℃以下再循环利用,存在能量利用不合理状况。薄膜装置现有2台螺杆式冷水机组,每台额定制冷量为1680kW,正常运行时制冷量约为额定制冷量的3/4,额定输入功率为350kW,所产冷冻水主要用于冷却电机齿轮箱、牵引辊等设备和降低厂房环境温度。经分析,可以在薄膜装置增上一台额定制冷量为1798kW的低温热水型溴化锂制冷机组,代替原环境空调用冷冻水机组,回收夏季富余的350t/h低温热水热量,生产出符合薄膜装置工艺要求的冷冻水。同时,就增上一台低温热水型溴化锂制冷机组后薄膜装置冷冻水系统运行方式进行可行性分析,并估算投资金额及经济效益。 相似文献
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《动力工程学报》2016,(9):704-710
基于高温风洞实验台,采用红外热成像技术和机械振动机构对振动平板单孔气膜冷却特性进行了实验研究.测量吹风比在0.4~1.8范围内,静态以及振动状态下的气膜冷却效果,并分析了振幅(0~5mm)和频率(0~20Hz)等因素对气膜冷却效果的影响.结果表明:振动会削弱气膜冷却效果;与频率相比,振幅对气膜冷却效果的影响更大;随着吹风比的增大,同一振动对气膜冷却效果的影响变小;频率不同的振动对气膜冷却效果的影响相近,在X/D=5~10内,平均有效温比降低约3%;振幅不同的振动对气膜冷却效果的影响是相近的,在X/D=5~10内,平均有效温比降低约5%. 相似文献
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气膜冷却是当代燃气轮机透平中重要的冷却手段,气膜冷却设计在透平设计中非常重要,而这就要求有快速、准确的气膜冷却预测方法。综述了国内外学者对不同孔型气膜冷却多参数影响机制的研究成果,比较了针对复杂气膜冷却系统的多种预测方法。发现经验公式法传统上应用广泛,但其精度受制于公式的适用范围;基于神经网络预测气膜冷却特性具有精度高、参数适用范围广的特点,采用CFD方法预测气膜冷却特性耗时较长,精度不高。结果表明神经网络法在工业应用上前景好,CFD法则需要对各向同性的湍流模型进行修正才能有效地开展气膜冷却机理研究。 相似文献
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Ki-Don Lee 《Numerical Heat Transfer, Part A: Applications》2013,63(4):362-380
Optimization of a cylindrical film-cooling hole has been performed by surrogate modeling approach using three-dimensional Reynolds-averaged Navier-Stokes analysis. SST model has been employed as a turbulence closure model for the analysis of turbulent convective heat transfer. Spatially-averaged film-cooling effectiveness has been maximized for optimization. For two design variables, the ratio of length to the diameter of the hole and ejection angle, 12 experimental points are selected by Latin hypercube sampling. Performances of three basic surrogate models and three weighted average surrogate models have been evaluated. Among the surrogate models tested, the Kriging model predicts the optimum point with the highest objective function value calculated by Reynolds-averaged Navier-Stokes analysis, which gives a 3.6% improvement of the spatially-averaged film-cooling effectiveness in comparison to the reference geometry. The objective function is more sensitive to the ejection angle than the ratio of length to diameter of the hole. 相似文献