楔形仿螺旋肋片内冷通道的流动与换热

利用有限体积法对三维不可压缩的N-S方程进行离散,对上下表面带有错排间断性楔形肋片且对置的仿螺旋内冷通道进行了数值模拟。网格划分采用非结构化混合网格,湍流模型为kε-两方程模型,在近壁面处采用标准壁面函数法进行处理,速度和压力的耦合采用S IM PLE算法。计算获得了楔形仿螺旋肋片内冷通道在楔形肋片与主流方向夹角分别为0°、15°、30°时的三维流场分布。结果表明楔形仿螺旋肋片内冷通道的流场结构比较复杂,通道内流体流动达到了预期的仿螺旋流动效果。通道的平均努谢尔数随楔形肋片与主流夹角的增大而呈增大趋势,通道换热强度得到了明显的提高,但同时流动阻力也显著增加。     

矩形肋片导流角度对内冷通道流动与换热特性的影响

利用数值模拟方法分析了矩形仿螺旋肋片内冷通道中肋片导流角度对内冷通道三维流场特性、换热特性以及流动阻力特性的影响。数值计算结果表明,肋片导流角度对内冷通道的流动与换热特性具有较大的影响。流场中冷却介质螺旋流动的强度随着肋片导流角增大而增强,肋片导流角度越大则内冷通道的换热强度越强,同时通道中流动阻力也明显增大。从内冷通道的综合换热效果来看,当肋片导流角度为7。时,矩形仿螺旋肋片内冷通道的综合换热效果最好。     

有扰流片的矩形通道内空气流动和传热过程的数值模拟

以高温透叶片尾部区内部冷却为应用背景，对带顺排、错排扰流片肋的通道内空气流动和传热过程进行了数值模拟。计算结果表明，在相同雷诺数下，错排扰流片的阻力系数比针肋和顺排绕流片的阻力因子均增大约2%，而冷却能力分别增大约50%和9%。     

螺旋肋片管省煤器的结构特点及传热计算

本文介绍了国内外螺旋肋片管省煤器的典型结构特点，并对不同布置型式的性能特点进行分析，综合国外设计计算方法进行分析、比较、整理。从而推荐一套具有适用价值的传热公式，并针对影响沾污系数，传热系数的各种因素进行了较深入的分析。     

内部通道肋片结构对Mark Ⅱ叶片冷却性能影响的降维模型研究

一维冷却通道气热耦合计算是分层涡轮叶片冷却结构设计的重要方法。发展了以管道网络算法为核心的内部冷却特性计算程序,并与三维传热计算进行了耦合。通过与MarkⅡ叶片特定实验工况下的结果进行对比,验证了方法的有效性。此外,进一步将带肋结构流道传热特性相关经验公式集总在一维气热耦合算法中,分析了带肋通道改型的MarkⅡ叶片冷却性能。结果显示,带肋结构相比光滑流道能显著提升换热性能,在中径截面处较原方案温度下降15～30 K。     

组合肋通道流动与传热特性的数值分析

本文采用数值模拟的方法研究了一种新型组合肋通道的流动与传热特性,主要对比了不同肋型通道的传热性能和阻力性能,考察了雷诺数、肋间距和肋高对通道壁面特征数的影响规律.结果 表明与矩形肋、半圆肋通道相比,组合肋通道的综合传热性能最好,且阻力损失小.     

带扰流片的矩形直通道内的流动与换热

建立了矩形直通道内三维可压缩流动与换热模型 ,对来流雷诺数Re在 1× 10 5～ 3× 10 5范围内 ,带顺排和错排扰流片的通道内部对流换热过程进行了模拟计算。计算结果表明 ,矩形扰流片具有明显的强化冷却效果 ,扰流片表面的对流换热系数明显高于光滑表面的值 ,有扰流片区域的壁面温度明显降低 ;错排扰流片与顺排扰流片相比 ,对流换热系数增大 4 %左右。计算结果归纳了传热和流动压降关系式。     

基于CFD DEM微细带肋内冷通道中颗粒沉积特性比较研究

航空发动机全天候全域长航时运行时,颗粒随着二次流空气系统进入到涡轮叶片内部,沉积堵塞在涡轮叶片内冷通道中,严重影响了涡轮叶片的冷却性能。本文采用计算流体力学和离散单元法(CFD-DEM)相结合的方法研究了涡轮叶片带肋细小矩形内冷通道中微尘颗粒的流动和沉积特性。所研究的内冷通道肋片周期性布置在通道的一侧,肋片阻塞比和肋间距比分别为0.024和10,考虑了平行直肋、45°斜肋和45°V肋3种肋结构,详细分析了雷诺数、颗粒斯托克斯数、入口颗粒体积分数和肋片的类型对颗粒流动和沉积特性的影响规律。结果表明：颗粒沉积主要发生在第1根肋片的前缘处;颗粒的沉积质量均随着雷诺数、斯托克斯数和颗粒体积分数增加而减小;在所有的肋片类型中,直肋布置时颗粒沉积现象最明显,其次是V肋,斜肋拥有最小的颗粒沉积质量。     

螺旋肋片管在35t／h锅炉省煤器上的应用及传热计算

介绍了螺旋肋片管省煤器在３５ｔ／ｈ锅炉上的应用，推荐了合理可行的传热计算公式。     

不同宽高比旋转方形通道内部流体流动与换热的数值研究

分析了不同宽高比截面的燃气轮机涡轮叶片内冷径向出流通道模型,对其内部流体的流动与换热进行了数值模拟,计算工况为Re=25000、密度比△ρ／ρ=0．13、旋转数Ro=0．24。对比不同宽高比通道的计算结果得出：小宽高比的通道能够强化主流速度型向后缘的偏移,并且可以强化通道后缘表面的换热;在大宽高比的通道中,主流速度型向后缘的偏移减弱,哥氏力二次流漩涡向两侧偏移明显加剧,通道后缘表面的换热被削弱,通道前缘的换热有所增强。     

Experimental study on heat transfer and flow resistance in improved latticework cooling channels

Characteristics of heat transfer and flow resistance of the latticework （vortex） cooling channel with ribs truncated at their two ends were theoretically and experimentally studied compared with regular and smooth channels of the same configuration. The results showed： the heat transfer efficiency of the latticework channel with two slots was better than those of regular and smooth channels of the same configuration, its flow resistance situation in the slotted channel becomes quite complex; The flow resistances of 2 mm- and 4 mm-slotted channels were obviously lower than that of the regular channel, but they are still much higher than that of the smooth channel; Compared with the regular channel, the total heat transfer efficiencies of the slotted channels were pretty improved, among them the 4-mm slotted channel has the biggest enhancement. From the experimental results, it is obvious that the latticework channel with proper slots has a great prospect in the design of the inner cooling channels of turbine blades.     

Conjugate heat transfer investigation on the cooling performance of air cooled turbine blade with thermal barrier coating

A hot wind tunnel of annular cascade test rig is established for measuring temperature distribution on a real gas turbine blade surface with infrared camera. Besides, conjugate heat transfer numerical simulation is performed to obtain cooling efficiency distribution on both blade substrate surface and coating surface for comparison. The effect of thermal barrier coating on the overall cooling performance for blades is compared under varied mass flow rate of coolant, and spatial difference is also discussed. Results indicate that the cooling efficiency in the leading edge and trailing edge areas of the blade is the lowest. The cooling performance is not only influenced by the internal cooling structures layout inside the blade but also by the flow condition of the mainstream in the external cascade path. Thermal barrier effects of the coating vary at different regions of the blade surface, where higher internal cooling performance exists, more effective the thermal barrier will be, which means the thermal protection effect of coatings is remarkable in these regions. At the designed mass flow ratio condition, the cooling efficiency on the pressure side varies by 0.13 for the coating surface and substrate surface, while this value is 0.09 on the suction side.     

Fluid flow characteristics and convective heat transfer improvement on a gas turbine blade

The flow field features and heat transfer enhancement are investigated on a gas turbine blade by applying the jet impingement cooling method. The distribution of the flow field and the Nusselt number (Nu) was determined on the targeted surface in the cooling channel. The injection holes of different shapes, such as circular, square, and rectangular were considered. The Reynolds numbers (Re) of the airflow in the range of 2000–5000 and aspect ratios of 0.5–2 were particularly focused. The flow vortices and recirculation in the cooling channel and their influence on the heat transfer enhancement were analyzed in detail under different airflow and geometric conditions. Decreasing the ratio of the distance between jet-to-target plate to the diameter of the jet orifice (H/d) increased the heat transfer rate and produced high-intensity vortices and recirculation zones. It was noticed that the formation and generation of vortices and recirculation have important effects on the convective heat transfer rate at the impingement surface. Local Nusselt number, formation of complex vortices, and airflow recirculation in the cooling channel decreased with the increase in the distance between the jet hole and the targeted surface. It was found that with the increase in the Reynolds number of the jet, heat transfer between cold airflow and the targeted surface increased. Moreover, it was observed that the cooling performance of the round and square jet holes was better than the rectangular holes.     

冷却通道参数对发汗冷却性能影响的数值研究

为了解决传统多孔材料孔隙结构不可控的问题,制备具有可控微冷通道的冷却结构对提高涡轮叶片冷却效率有着重要意义。为了研究不同冷却通道参数对叶片发汗冷却效率的影响,通过数值模拟方法研究了不同注入比下,仿生树形通道和传统直孔通道发汗冷却多孔板的换热特性及流动机理。同时,研究了6种不同模型参数多孔板在不同注入比下的冷却性能及流场的变化情况。研究结果表明：在内表面比和冷却剂出口面积基本一致的条件下,仿生树形多孔板具有更高的冷却效率;当注入比为2%时,仿生树形多孔板的平均冷却效率提高了5%,且存在一个最佳的注入比使得整体的冷却效率最高;冷却剂的出口面积是影响发汗冷却效率的关键性独立参数,与冷却剂的注入比大小有关;孔隙率对整体的冷却效率影响较小,内表面积比越大,发汗冷却的整体冷却效率越高。     

叉排针肋楔型通道换热数值研究

应用湍流模型对涡轮叶片尾缘叉排针肋通道的换热与流动进行了三维数值模拟研究。为了研究冷却叶片尾缘处正压面与背压面之楔角对通道换热与流动的影响 ,在通道楔角θ为 0°～ 2 0°进行了数值模拟计算 ;为了研究 Reynolds数对通道换热与流动的影响 ,在 Re为 0 .5× 10 4～ 4 .0× 10 4进行了数值模拟计算。最后给出了一个最佳楔角     

Influence of internal channel geometry of gas turbine blade on flow structure and heat transfer

This paper presents the study of the influence of channel geometry on the flow structure and heat transfer,and also their correlations on all the walls of a radial cooling passage model of a gas turbine blade.The investigations focus on the heat transfer and aerodynamic measurements in the channel,which is an accurate representation of the configuration used in aeroengines.Correlations for the heat transfer coefficient and the pressure drop used in the design of internal cooling passages are often developed from simplified models.It is important to note that real engine passages do not have perfect rectangular cross sections,but include a comer fillets,ribs with fillet radii and a special orientation.Therefore,this work provides detailed fluid flow and heat transfer data for a model of radial cooling geometry which has very realistic features.     

Laminar convective heat transfer in a microchannel with internal longitudinal fins

A numerical study was conducted to investigate the fluid flow and heat transfer characteristics of a square microchannel with four longitudinal internal fins. Three-dimensional numerical simulations were performed on the microchannel with variable fin height ratio in the presence of a hydrodynamically developed, thermally developing laminar flow. Constant heat flux boundary conditions were assumed on the external walls of the square microchannel. Results of the average local Nusselt number distribution along the channel length were obtained as a function of the fin height ratio. The analysis was carried out for different fin heights and flow parameters. Interesting observations that provide more physical insight on this passive enhancement technique, and the existence of an optimum fin height are brought out in the present study.     

Flow structure and heat exchange analysis in internal cooling channel of gas turbine blade

This paper presents the study of the flow structure and heat transfer, and also their correlations on the four walls of a radial cooling passage model of a gas turbine blade. The investigations focus on heat transfer and aerodynamic measurements in the channel, which is an accurate representation of the configuration used in aeroengines. Correlations for the heat transfer coefficient and the pressure drop used in the design of radial cooling passages are often developed from simplified models. It is important to note that real engine passages do not have perfect rectangular cross sections, but include corner fillet, ribs with fillet radii and special orientation. Therefore, this work provides detailed fluid flow and heat transfer data for a model of radial cooling geometry which possesses very realistic features.