基于响应曲面法的交错肋换热特性研究

为了深入了解交错肋进口雷诺数在104量级的换热特性,研究了肋倾角、肋宽与肋间距比和进口雷诺数对交错肋换热特性的影响。基于响应曲面法建立了交错肋回归模型,对数值模拟结果进行分析。研究发现各因素对交错肋换热性能的影响力为:肋倾角>肋宽与肋间距比>进口雷诺数。肋倾角减小,交错肋平均努塞尔数先增大后减小,肋倾角在30°~40°时平均努塞尔数出现极大值,肋倾角太小不利于换热。肋倾角每减小25°时,交错肋流阻系数平均增大10倍;当肋倾角增大时,交错肋流阻系数极大值向低雷诺数方向移动;当肋倾角大于35°时,肋宽与肋间距比和进口雷诺数对交错肋流阻系数影响较小。进口雷诺数与交错肋换热性能参数均呈正相关。交错肋在大肋宽与肋间距比、小肋倾角时的换热能力更强;在大肋宽与肋间距比、大肋倾角时的综合流动传热性能更好。

Investigation of influencing factors of hot streaks migration in high pressure stage of a vaneless counter-rotating turbine

Three-dimensional,viscous,and unsteady CFD simulations have been performed in order to reveal the influencing factors of hot streaks migration in high pressure stage of a vaneless counter-rotating turbine. Based on the numerical results,the comparison between the case with inlet hot streaks and case without inlet hot streaks is carried out,which shows that the effect of inlet hot streaks on the load distributions of high pressure turbine airfoils is not notable and the airfoil load distributions are directly related to the inlet pressure distributions. The predicted results also indicate that the circumferential and radial movements of the hot streaks were not observed in the high pressure turbine stator. This means that the combined effects of secondary flow and buoyancy are very weak in the high pres-sure turbine stator. The numerical results also prove that the circumferential flow angle effect at the inlet of the high pressure turbine rotor,secondary flow effect and buoyancy effect are the mainly influencing factors to directly affect the migration characteristics of the hot streaks in the high pressure turbine rotor.

Influence of exit-to-throat width ratio on performance of high pressure convergent-divergent rotor in a vaneless counter-rotating turbine

This paper describes the redesign of a high pressure rotor (with exit Mach number around 1.5) for the vaneless counter-rotating turbine by choosing adequate exit-to-throat width ratio. Based on the previous design analysis and test results, effects of the exit-to-throat width ratio on the performance of the transonic turbine cascade were proposed. In order to investigate the influence of the exit-to-throat width ratio on the performance of the turbine cascade, a flow model of the convergent-divergent turbine cascade was constructed by using the theory of Laval nozzle. Then a method on how to choose the adequate exit-to-throat width ratio for the turbine cascade was proposed. To validate the method, it was used to calculate the adequate exit-to-throat width ratio for the high pressure rotor of the vaneless counter-rotating turbine. The high pressure turbine rotor was redesigned with the new exit-to-throat width ratio. Numerical simulation results show that the isentropic efficiency of the redesigned vaneless counter-rotating turbine under the design condition has increased by 0.9% and the efficiencies under the off-design conditions are also improved significantly. On the original design, a group of compressional waves are created from the suction surface after about 60% axial chord in the high pressure turbine rotor. While on the new design the compressional waves are eliminated. Furthermore, on the original design, the inner-extending waves first impinge on the next high pressure turbine rotor suction surface. Its reflection is strong enough and cannot be neglected. However on the new design the inner-extending waves are weakened or even eliminated. Another main progress is that the redesigned high pressure turbine rotor is of practical significance. In the original rotor, a part of the blade (from 60% axial chord to the trailing edge) is thin leading to the intensity problem and difficult arrangement of the cooling system. In the new design, however, the thickness distribution of the rotor airfoil along the chord is relatively reasonable. The intensity of the rotor is enhanced. It is possible to arrange the cooling system reasonably.

Experimental investigation on unsteady pressure fluctuation of rotor tip region in high pressure stage of a vaneless counter-rotating turbine

An experimental investigation has been performed to study the unsteady pressure fluctuation of rotor tip region in high pressure stage of a vaneless counter-rotating turbine.The experiment is carried out on a blow-down short duration turbine facility.The investigation indicates that the blow-down short duration turbine facility is capable of substituting continuous turbine facilities in most turbine testing.Through this experimental investigation,a distinct blade-to-blade variation is observed.The results indicate that the combined effects of vane wake,tip leakage flow,complicated wave systems and rotor wake induce the remarkable blade-to-blade variations.The results also show that the unsteady effect is intensified along the flow direction.

Study on topology and vortex structure in a diffusion cascade

To further make clear vortex structures in diffusion cascades so as to help understand the mechanisms of vortex affecting loss production, the emergence, evolution and development of secondary flow vortexes, including horse shoe vortex, passage vortex and corner vortex and so on, were discussed mainly through using the topological analysis method and numerical calculation. The concept of a three-dimensional dividing surface between the low energy flow zone and the exterior flow zone was presented. The results show that concentrated shed vortex is located outside the dividing surface (in the outer flow zone) and horse shoe vortex, passage vortex and corner vortex are inside the dividing surface (in the low energy flow zone). Dissipation function is used to measure loss production instead of using entropy production. The results about loss analysis indicate that vortex motion directly causes loss production, namely, peak value of loss is generally located around the core of vortex and that maximal loss happens around the dividing surface other than in the low energy flow zone.

Stream Surface Theory of Bird-like Flapping Flight

Through analyzing the motion characteristics of bird-like flapping flight, it is considered that the wing angular acceleration is equal to zero at the point of maximum angular speed. Thus, the flapping flight is equivalent to a uniform rotating motion which can be analyzed by using the stream surface theory of turbomachinery during a micro period of time. In this article, the N-S equations of the motion are expanded in a non-orthogonal curvilinear coordinate system, and simplified on stream surfaces of the flapping flight model. By using stream function method, the three-dimensional unsteady flow equations are simplified as a two-order partial differential equation with variable coefficients eventually and the equation's iterative solving method on S1 and S2 stream surfaces of the flapping flight model is presented. Through expanding the relatively steady equations of flapping flight at an arbitrary time point of a stroke on meridional plane of the flapping flight model, it can use a relatively steady motion to approximate the real flapping flight at that time point, and analyze the flow stability influenced by the wing's flexibility. It can be seen that the wing flexibility is related to the higher pressurization capacity and the flow stability, and the pressurization capacity of flexible wing is proportional to the angular speed, angular distortion rate and radius square.

Influence of Tip Clearance on Centrifugal Compressor IGV Regulation and Improvement

In order to avoid collision with the end wall of the casing when the guide vane rotates around its own rotating axis in a centrifugal compressor,a circular gap will be left at the top of guide vane.Part of the gas flow through the clearance cannot be effectively regulated,and the tip clearance leakage vortex is formed,which has an impact on the mainstream and makes the compressor performance decline.In order to solve this problem,in this paper,three improved schemes of guide vane channel structure,including rectangular channel,cambered channel,and globular channel,were put forward,which can effectively improve the regulation ability of guide vane.Comparing these three improved channels with the original one,the stable operating range of the compressor was enlarged;the power consumption of the compressor was reduced and the efficiency of the compressor was improved.By comprehensive comparison,the cambered channel has better performance and is easier to process,which has potential to be widely used in practice.