Optimization of a stepped circular pin-fin array to enhance heat transfer performance

A Stepped circular pin-fin array is formulated numerically and optimized with Kriging metamodeling technique to enhance heat transfer performance. The problem is defined by two non-dimensional geometric design variables composed of height of the channel, height of smaller diameter part of the pin-fins, and smaller diameter of the pin-fins, to maximize heat transfer rate compromising with friction loss. Ten designs generated by Latin hypercube sampling were evaluated by three-dimensional Reynolds-averaged Navier–Stokes solver and the evaluated objectives were used to construct the surrogate model. The predictions of objective function by Kriging model at optimum point show reasonable accuracy in comparison with the values calculated by RANS analysis. Optimum shape of pin-fins strongly depends on the weighting factor which measures importance of the friction loss term in the objective function. The thermal performances are much higher than that of the straight pin-fin at sampling optimum points with different weighting factors.     

A comparative analysis of various shaped film-cooling holes

In the present work, numerical analysis has been performed to investigate the film-cooling performance of various film-cooling hole schemes such as fan, crescent, louver, and dumbbell-shaped holes. To analyze the turbulent flow and the film-cooling mechanism, three-dimensional Reynolds-averaged Navier–Stokes analysis has been performed with the shear stress transport turbulence model. The validation of the numerical results for the film-cooling effectiveness has been performed in comparison with experimental data. The film-cooling performance for each hole shape has been evaluated in terms of the centerline, laterally averaged, and spatially averaged film-cooling effectiveness values. The dumbbell-shaped hole shows the best spatially averaged film-cooling effectiveness for all blowing ratios tested in this work.     

Velocity and concentration field measurements and large eddy simulation of a shaped film cooling hole

The 3D velocity and scalar concentration fields from a laidback fan-shaped film cooling hole are measured using Magnetic Resonance Velocimetry (MRV) and Magnetic Resonance Concentration (MRC). The velocity and scalar concentration fields of the same geometry are also obtained using Large Eddy Simulation (LES). The geometry under consideration features a single film cooling hole with a 30° inclination angle and 7° forward and lateral expansion angles. The results are compared to an existing adiabatic effectiveness experiment using infrared imaging of an identical geometry (Schroeder and Thole, 2014). Flow separation is observed inside the hole in the LES and MRV. The separated region in the LES is symmetrically located, but it is offset to a lateral side in the MRV which slightly skews the scalar concentration field to one side. Comparisons of the LES with the MRV and MRC experiments show good agreement in the velocity and scalar concentration field elsewhere throughout the 3D domain. Despite some disagreement in the adiabatic effectiveness values with the IR experiment immediately after injection, there is good agreement downstream of injection between the IR experiment and the LES and MRC. Differences in the concentration field can be attributed to differences in the in–hole velocity field. The results suggest that the mean position of the region of separation inside the hole is geometrically sensitive.     

Multi-objective optimization of a guide vane in the turning region of a rotating U-duct to enhance heat transfer performance

An optimization has been performed for the design of a guide vane in the turning region of a rotating U-duct using the Kriging meta-model and a hybrid multi-objective evolutionary algorithm. Rotation of the U-duct is accompanied by the Coriolis force that causes a discrepancy in heat transfer between the trailing (pressure) and leading (suction) surfaces of the duct. For the optimization, three geometric variables related to the thickness, angle, and location of the guide vanes are selected as the design variables. A Kriging model is constructed to obtain a Pareto-optimal front through a multi-objective evolutionary algorithm. The values of the objective function at the design points are evaluated by Reynolds-averaged Navier–Stokes analysis. The shear stress transport model is used as the turbulence closure model in the analysis. The tradeoff between the two competing objective functions is discussed for Pareto-optimal solutions in the design space. The optimized guide vanes show an increase in heat transfer performance with a decrease in the friction loss in the turning region and downstream straight passage in comparison with the reference design.     

Optimization of an inclined elliptic impinging jet with cross flow for enhancing heat transfer

This work presents a parametric study and optimization of a single impinging jet with cross flow to enhance heat transfer with two design variables. The fluid flow and heat transfer have been analyzed using three-dimensional compressible Reynolds-averaged Navier–Stokes equations with a uniform heat flux condition being applied to the impingement plate. The aspect ratio of the elliptic jet hole and the angle of inclination of the jet nozzle are chosen as the two design variables, and the area-averaged Nusselt number on a limited target plate is set as the objective function. The effects of the design variables on the heat transfer performance have been evaluated, and the objective function has been found to be more sensitive to the angle of inclination of the jet nozzle than to the aspect ratio of the elliptic jet hole. The optimization has been performed by using the radial basis neural network model. Through the optimization, the area-averaged Nusselt number increased by 7.89% compared to that under the reference geometry.     

Detached eddy simulation of blade trailing-edge cutback cooling performance at various ejection slot angles

Detached eddy simulation (DES) has been carried out to study a three-dimensional trailing-edge (TE) cutback turbine blade model with five rows of staggered circular pin-fin arrays inside the cooling passage, in order to evaluate the cooling performance in relation to coolant ejection slot angle. Simulations were performed by adopting a shear-stress transport k-ω turbulence model, and the effects of three different ejection slot angles 5°, 10° and 15° were investigated in terms of the characteristics of adiabatic film-cooling effectiveness, coefficient of discharge, and vortex shedding frequencies, respectively. The results obtained have shown that the TE cutback blade cooling with a 5° coolant ejection slot angle produced a better heat transfer coefficient than the other two ejection slot angles tested. The distributions of adiabatic film-cooling effectiveness along the cutback walls were found to be sensitive to the coolant ejection slot angle, e.g. the increase of ejection slot angle to 15° yielded near unity of cooling effectiveness along the entire breakout walls, whereas the decrease of ejection slot angle caused a drastic decay of cooling effectiveness after the maximum effectiveness has been reached. Of the three angles studied, a TE cutback blade model with a 15° ejection slot angle produced an optimum film-cooling effectiveness. In the breakout region, vortex shedding was observed along the shear layer between the hot gas and the coolant airflow. The shedding frequencies were evaluated to be 2.93, 2.21, and 2.18 kHz for the ejection slot angles of 5°, 10° and 15°, respectively. The findings from this study could be useful to improve existing TE cutback turbine blade design to achieve optimum film-cooling performance.     

考虑材料非线性的两端固支柱后屈曲载荷优化算法

针对满足Ramberg-Osgood本构关系的6082-T6铝合金固支柱的后屈曲问题进行了研究。利用泰勒展开式得到了用于计算横截面上弯矩的应力显式表达式，并通过弯矩-曲率关系导出了用剪力表示的控制方程。由于同时考虑材料非线性和几何非线性，此时控制方程为二阶非线性微分方程，本文提出了求解包含屈曲载荷的控制方程的优化算法。以屈曲载荷和固支端处的曲率为设计变量，以固支柱中点处的转角和挠度形成目标函数。利用进退法和黄金分割法改变设计变量的值，通过程序中包含的R-K法输出不同的结果，然后将输出的结果代入到目标函数中进行比较，获得包含目标函数极小值的最小区间，最终实现了对满足计算精度的设计变量值的确定。相较于打靶法复杂的分析过程，该优化算法优化过程简单，计算速度较快。为了验证本文算法的正确性，与两端固支6082-T6铝合金柱后屈曲时的数值解进行了对比。     

基于Kriging的泡沫填充锥形薄壁结构耐撞性6σ稳健性优化设计

锥形薄壁结构的耐撞性设计过程中,其设计变量和噪声因素都具有一定的波动性,都存在不确定性.传统的优化设计方法由于忽略不确定因素的影响,当设计变量产生波动时,往往会引起设计最优目标超出约束界限或者目标函数对设计变量的波动极为敏感,从而导致设计失效.为了考虑参数的不确定影响,论文提出了一种结合试验设计技术、Kriging近似...     

基于断面形状优化的地铁车轮减振降噪研究

以降低地铁车辆在运行中产生的轮轨接触噪声为目的,将结构动力优化方法运用于地铁车轮断面外形设计,建立了地铁车轮振动噪声最优化设计的数学模型,编制了相应的算法程序.以我国某地铁车轮为例,给出了以车轮断面外形几何参数为设计变量、车轮结构振动辐射噪声值最小为目标函数的优化计算实例,得到了车轮断面外形几何参数在可行域内的最优解.结果表明,该优化设计方法是成功的,可以有效地降低车轮因振动而产生的噪声.     

Multi-objective optimization of discrete film hole arrangement on a high pressure turbine end-wall with conjugate heat transfer simulations

This paper discussed a method of combining a full automatic multi-objective optimization and conjugate heat transfer calculation to obtain optimal cooling layouts on a transonic high pressure guide vane under a realistic turbine working condition. The improvement in cooling design from the optimized models was analyzed in detail, along with a discussion of sensitivities of two objective functions to five design variables. The full automatic method comprises the process of geometry creation, mesh generation, numerical solution and post data analysis. The vane is solid and the end-wall is arranged in a linear cascade. On the end-wall, film holes are all cylindrical and classified in five regions, with region A near the leading edge of the vane, region B near the suction side, regions C and D near the pressure side, and region E for the rest. Five design variables are three pitch-to-hole ratios in regions B, D, E and two compound angles of film holes in regions A and D. Two selected objective functions are area averaged overall cooling effectiveness of the end-wall and aerodynamic losses in a cross-plane at x/C_ax = 1.06 just downstream of the outlet of the cascade. For the optimization process, the multi-objective genetic algorithm based on the Non-dominated Sorted Genetic Algorithm-II was applied. The Latin hypercube sampling method was used to choose 21 experimental design points in the design space, which are also the sources for constructing the surrogate models with the Kriging model. The results demonstrate that the method using full automatic optimization and conjugate heat transfer calculation has achieved an increase of 8.7%–9.5% in area-averaged overall cooling effectiveness and a reduction of about 4.8%–6.1% in aerodynamic losses. The highest increase in cooling effectiveness exists in the region near the pressure side with a mild increase in the middle of the passage. The largest heat flux reduction exists in the regions near the pressure side and the crown of the suction side. The change of compound angle in region A near the leading edge has a negligible influence on overall cooling effectiveness but a high impact on aerodynamic losses. It's advisable to maintain the compound angle and pitch-to-diameter ratio at low values in region D near the pressure side to obtain high cooling performance.