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High-fidelity CFD-trained machine learning to inform RANS-modelled interfacial turbulence 高保真的cfd训练机器学习,以通知ranss模型的界面湍流
Q4 ENGINEERING, MECHANICAL Pub Date : 2023-08-14 DOI: 10.33737/jgpps/166558
Bertolotti Luc, Richard Jefferson-Loveday, Stephen Ambrose, Evgenia Korsukova
In aero-engine bearing chambers, two-phase shearing flows are difficult to predict as Computational Fluid Dynamics (CFD) RANS models tend to overestimate interfacial turbulence levels, leading to inaccuracies in the modelling of the flow. Turbulence damping methods have been developed to address this problem, such as Egorov’s correction, however, this method is mesh dependent and results differ considerably according to the choice of turbulence damping coefficient. In addition, this approach assumes a smooth interface between the air and oil phases when in reality they are wavy. In this paper, a Machine Learning method is used to inform an unsteady RANS turbulence modelling. It is trained using high fidelity quasi-DNS simulation data and used to provide an appropriate correction to the popular Wilcox’s standard RANS kω turbulence model. The correction consists of a machine learning-predicted source term which is used to adjust the energy budget in the RANS transport equations. Demonstration of the approach is presented for a range of interfacial flow regimes.
在航空发动机轴承室中,由于计算流体动力学(CFD) RANS模型往往会高估界面湍流水平,导致两相剪切流难以预测,从而导致流动建模不准确。为了解决这一问题,已经发展了湍流阻尼方法,例如Egorov的校正,然而,这种方法依赖于网格,并且根据湍流阻尼系数的选择结果差异很大。此外,这种方法假设空气和油相之间有一个平滑的界面,而实际上它们是波浪状的。本文采用机器学习方法建立了非定常RANS湍流模型。它使用高保真准dns模拟数据进行训练,并用于对流行的Wilcox标准RANS <inline-formula><mml:math xmlns:mml="http://www.w3.org/1998/Math/MathML" display="inline" overflow="scroll"><mml: m>k</mml: m>< - </mml: m></mml: m>ω</mml: m></mml:math></ mml:math></inline-formula>湍流模型。修正由一个机器学习预测源项组成,该源项用于调整RANS输运方程中的能量收支。该方法的演示提出了一系列的界面流动状态。
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引用次数: 0
Development of a surrogate model for uncertainty quantification of compressor performance due to manufacturing tolerance 基于制造公差的压缩机性能不确定性量化替代模型的建立
Q4 ENGINEERING, MECHANICAL Pub Date : 2023-08-04 DOI: 10.33737/jgpps/168293
Quentin Rendu, Loic Salles
In gas turbines and jet engines, stagger angle and tip gap variations between adjacent blades lead to the deterioration of performance. To evaluate the effect of manufacturing tolerance on performance, a CFD-based uncertainty quantification analysis is performed in this work. However, evaluating dozens of thousands of rotor assembly through CFD simulations would be computationally prohibitive. A surrogate model is thus developed to predict compressor performance given an ordered set of manufactured blades. The model is used to predict the influence of tip gap and stagger angle variations on maximum isentropic efficiency. The results confirm that the best arrangement is obtained by minimizing the stagger angle variation between adjacent blades, and by maximizing the tip gap variation. Another finding is that the best arrangement yields the lowest variability, the range of maximum efficiency being 4 times sharper (resp. 2 times) than worst arrangement for stagger angle variations (resp. tip gap variations). Not measuring manufacturing tolerance, or not specifying any strategy for the blade arrangement, lead to variability as large as the worst arrangement.
在燃气轮机和喷气发动机中,相邻叶片之间的交错角和叶尖间隙的变化会导致性能的恶化。为了评估制造公差对性能的影响,本文进行了基于cfd的不确定性量化分析。然而,通过CFD模拟来评估成千上万的转子组件在计算上是令人望而却步的。因此,开发了一个代理模型来预测给定一组订购的制造叶片的压气机性能。利用该模型预测了叶尖间隙和错开角变化对最大等熵效率的影响。结果表明,最大限度地减小相邻叶片间的交错角变化,最大限度地增大叶尖间隙变化,可以获得最佳的布置方式。另一个发现是,最佳的排列方式产生最小的变异性,最高效率的范围是原来的4倍。2倍)比最差安排的交错角度变化(如。尖端间隙变化)。不测量制造公差,或不指定任何策略的叶片安排,导致变异性大到最差的安排。
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引用次数: 1
Coking of gas turbine lubrication oils at elevated temperatures 燃气轮机润滑油在高温下的焦化
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-08-04 DOI: 10.33737/jgpps/168292
Raquel Juárez, E. Petersen
Over the last several decades, turbine efficiency has improved significantly, resulting in higher turbine operating temperatures that negatively affect the lubricating oil circulating through the system. Exposure to high temperatures results in oil degradation and the eventual formation of solid deposits in the oil which greatly limit the oil’s ability to reduce wear and cool the turbine components. An experimental apparatus was designed and built to allow for the studying and better understanding of this phenomenon. The apparatus consists of a flow loop with a heated test section through which the oil is pumped. The oil that comes into contact with the hot surfaces degrades and forms solid deposits. As time passes, the deposit buildup decreases the heat transfer that occurs at the test section. The bulk oil temperatures into and out of the test section are used as indicators of the deposit induction time and buildup rate, and the deposits may be analyzed at the end of the experiment. Air or an inert gas may be used to pressurize the system up to 69 bar, while test section surface temperatures may be as high as 650°C. Data from one of the initial tests performed with the apparatus using a gas turbine lube oil are included in this paper. The test resulted in the clear formation of solid deposits on the heated surfaces and in the data that show the decrease in the bulk oil temperature over time due to their formation. Assembly and testing of the apparatus have been completed, and it is now fully operational and ready for future studies on lubricating oil thermal degradation and oxidation.
在过去的几十年里,涡轮机效率显著提高,导致涡轮机运行温度升高,对系统中循环的润滑油产生负面影响。暴露在高温下会导致机油退化,并最终在机油中形成固体沉积物,这大大限制了机油减少磨损和冷却涡轮机部件的能力。为了研究和更好地理解这一现象,设计并建造了一个实验装置。该装置由一个带有加热测试段的流动回路组成,通过加热测试段泵送机油。与热表面接触的机油会降解并形成固体沉积物。随着时间的推移,沉积物的堆积减少了在测试段发生的热传递。进入和离开测试段的散装油温度被用作沉积物诱导时间和堆积速率的指标,并且可以在实验结束时分析沉积物。空气或惰性气体可用于将系统加压至69巴,而试验段表面温度可能高达650°C。本文包括使用燃气轮机润滑油对设备进行的一次初始测试的数据。试验结果表明,加热表面上明显形成了固体沉积物,数据显示,随着时间的推移,由于固体沉积物的形成,散装油温度降低。该装置的组装和测试已经完成,目前已全面投入使用,可用于未来润滑油热降解和氧化的研究。
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引用次数: 0
Development of metal AM technology for gas turbine components 燃气轮机部件金属AM技术的发展
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-07-27 DOI: 10.33737/jgpps/163429
Shuji Tanigawa, Masahito Kataoka, M. Taneike, Ryuta Ito, Takanao Komaki, Norihiko Motoyama
Mitsubishi Heavy Industries, Ltd. (MHI) Group has been developing additive manufacturing (AM) as a method that can manufacture parts with complex shapes and considering its application to manufacturing processes. In combustor components, application of AM process to rapid prototyping and multi-cluster nozzles for hydrogen or ammonia gas fuel is being considered. In turbine parts, with the aim of improving performance by reducing the amount of cooling air, the adoption of a complex internal cooling structure, which cannot be made with conventional manufacturing methods but can only be made by AM, is being considered. This paper describes design for AM technology for gas turbine components and metal AM process technology such as building simulation based high stiffness support design and pre-set distortion, microstructure control by laser scanning conditions, quality control through in-process monitoring tools and application of AM technology to gas Turbine Components.
三菱重工集团(MHI)一直在开发增材制造(AM),作为一种可以制造复杂形状零件的方法,并考虑将其应用于制造过程。在燃烧室部件中,正在考虑将AM工艺应用于快速成型和氢气或氨气燃料的多簇喷嘴。在涡轮部件中,为了通过减少冷却空气量来提高性能,正在考虑采用传统制造方法无法制造而只能通过增材制造制造的复杂内部冷却结构。本文介绍了燃气轮机部件的增材制造技术设计和金属增材制造工艺技术,如基于建筑模拟的高刚度支撑设计和预设定变形、激光扫描条件的微结构控制、通过过程监控工具的质量控制以及增材制造技术在燃气轮机部件上的应用。
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引用次数: 0
Variability in additively manufactured turbine cooling features 额外制造的涡轮机冷却特性的可变性
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-07-27 DOI: 10.33737/jgpps/162654
Alexander Wildgoose, K. Thole
Additive manufacturing (AM) allows for the rapid fabrication of complex components relative to conventional fabrication methods aiding in the development and testing of advanced turbine cooling methods. The repeatability of printed geometric features in the same part is required to maintain part quality, flow, and heat transfer. It is widely understood as to the impact that the additional roughness of AM provides with regards to part quality, but part variability also leads to differences in performance either locally in considering a single airfoil or globally when considering an entire stage. Previous studies have shown the importance of certain process parameters, build directions, and feature sizes on the part quality when printing a part using AM. As processes have continued to evolve, other artifacts of AM have arisen such as the location on the build plate. This article highlights the progress that has been made on printing commonly used cooling features by either considering simple straight coupons or a curved vane leading edge. Also discussed is the variability that exists and the resulting convective heat transfer and pressure losses. Results indicate that the variation of roughness between components and the part-to-part variations increased the further the component was from the laser source on the build plate. Similarly, the variation and levels in the pressure loss and heat transfer of the cooling channels also increased when samples were placed further from the laser source on the build plate.
增材制造(AM)允许相对于传统制造方法快速制造复杂部件,有助于开发和测试先进的涡轮机冷却方法。同一零件中印刷几何特征的可重复性是保持零件质量、流量和传热所必需的。AM的额外粗糙度对零件质量的影响已被广泛理解,但零件可变性也会导致性能差异,无论是在考虑单个翼型时的局部差异,还是在考虑整个阶段时的全局差异。先前的研究表明,当使用AM打印零件时,某些工艺参数、构建方向和特征尺寸对零件质量的重要性。随着工艺的不断发展,AM的其他伪影也出现了,如构建板上的位置。本文重点介绍了通过考虑简单的直试样或弯曲的叶片前缘,在打印常用冷却功能方面取得的进展。还讨论了存在的可变性以及由此产生的对流传热和压力损失。结果表明,部件之间的粗糙度变化以及部件间的变化随着部件离构建板上的激光源越远而增加。类似地,当样品被放置在离激光源更远的构建板上时,冷却通道的压力损失和热传递的变化和水平也增加。
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引用次数: 2
Editorial: Some Advances in Additive Manufacturing for Aerothermal Technologies 社论:空气热技术增材制造的一些进展
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-07-27 DOI: 10.33737/jgpps/168474
Li He
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引用次数: 0
Fundamentals and recent progress of additive manufacturing-assisted porous materials on transpiration cooling 增材制造辅助多孔材料蒸发冷却的基本原理及最新进展
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-07-27 DOI: 10.33737/jgpps/166418
R. Xu, Zhilong Cheng, Peixue Jiang
The requirements for new generation vehicles in terms of the flight speed, thrust–weight ratio, and maneuverability necessitate the development of high performance and reliable propulsion systems where active thermal protection technology plays a crucial role. Transpiration cooling based on a microporous structure is considered as one of the most promising techniques for protecting the high heat flux walls from ablation in aerospace applications. Unlike conventional fabrication methods, additive manufacturing (AM) has been applied to fabricate three-dimensional (3D) porous structures with customized geometries that are specific to applications, i.e., in terms of the design of features such as the pore diameter, pore density, porosity, and pore morphology. Three major AM technologies (selective laser melting, inkjet, and stereolithography) followed by a post-printing process have been proposed for the additive manufacture of porous structures. In particular, 3D-printed porous structures have great promise for transpiration cooling applications. In this review, we discuss the detailed steps of porous structure topology design and a general framework is presented for AM. The heat transfer and strength performance are also provided for porous parts fabricated by AM. Furthermore, the applications of 3D-printed porous media in transpiration cooling with different regimes are described. This review concludes by explaining the current challenges and prospects for the next generation of 3D-printed porous structures in transpiration cooling systems.
新一代飞行器在飞行速度、推重比和机动性方面的要求要求研制高性能、可靠的推进系统,主动热防护技术在其中起着至关重要的作用。基于微孔结构的蒸腾冷却被认为是保护高热流密度壁免受烧蚀的最有前途的技术之一。与传统的制造方法不同,增材制造(AM)已经被应用于制造具有特定应用的定制几何形状的三维(3D)多孔结构,即在孔径、孔隙密度、孔隙率和孔隙形态等特征的设计方面。三种主要的增材制造技术(选择性激光熔化、喷墨和立体光刻)以及后印刷工艺已经被提出用于多孔结构的增材制造。特别是,3d打印多孔结构在蒸腾冷却应用方面具有很大的前景。在这篇综述中,我们讨论了多孔结构拓扑设计的详细步骤,并提出了AM的总体框架。还提供了增材制造多孔零件的传热和强度性能。此外,还介绍了3d打印多孔介质在不同机制下的蒸腾冷却中的应用。这篇综述最后解释了当前的挑战和下一代3d打印多孔结构在蒸腾冷却系统中的前景。
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引用次数: 0
Isotropic and anisotropic mesh adaptation for RANS simulations of a nacelle under crosswind conditions 侧风条件下机舱RANS模拟的各向同性和各向异性网格自适应
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-06-30 DOI: 10.33737/jgpps/162640
Billon Laure, Papadogiannis Dimitrios, Alauzet Frédéric
Mesh adaptation of unstructured meshes for aerodynamic simulations, that typically resolve the Reynolds Averaged Navier-Stokes (RANS) equations, is a promising approach to enable high numerical precision on complex geometries. Its objective is to minimize the discretization error without using empirical meshing guidelines. The most common approach of mesh adaptation is the “feature-based” isotropic mesh adaptation: from an initial flow prediction on an isotropic unstructured mesh, a local error estimator is computed using a flow variable. It is then used to adapt the mesh using isotropic tetrahedra. Additional near-wall resolution can be achieved by extruding prism layers from the walls. A more efficient approach is to use anisotropic mesh adaptation purely with tetrahedra that are stretched to follow the flow's preferential directions. In this work, we demonstrate the abilities of feature-based isotropic and anisotropic mesh adaptation on a complex flow phenomenon of importance for jet engines: flow separation in a nacelle under crosswind conditions. Two different solvers, adapted for either isotropic or anisotropic meshes, are employed. Results are compared with standard unstructured simulations with user-imposed mesh refinements and highlight the ability of mesh adaptation to automatically capture all the relevant flow phenomena without any user input and at reduced mesh size.
用于空气动力学模拟的非结构化网格的网格自适应,通常解决雷诺平均纳维-斯托克斯(RANS)方程,是在复杂几何形状上实现高数值精度的一种很有前途的方法。其目标是在不使用经验网格准则的情况下最小化离散化误差。网格自适应最常见的方法是“基于特征”的各向同性网格自适应:从各向同性非结构化网格上的初始流量预测,使用流量变量计算局部误差估计器。然后使用它来调整使用各向同性四面体的网格。额外的近墙分辨率可以通过从墙上挤出棱镜层来实现。一种更有效的方法是纯粹使用各向异性网格自适应,四面体被拉伸以遵循流动的优先方向。在这项工作中,我们展示了基于特征的各向同性和各向异性网格对喷气发动机重要的复杂流动现象的适应能力:侧风条件下机舱中的流动分离。采用两种不同的求解器,适用于各向同性或各向异性网格。将结果与具有用户强加的网格细化的标准非结构化模拟进行比较,并强调了网格自适应的能力,即在没有任何用户输入的情况下以减小的网格尺寸自动捕捉所有相关的流动现象。
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引用次数: 0
Experimental investigation of the influence of film cooling hole diameter on the total cooling effectiveness for cyclone-cooled turbine blades 旋流冷却涡轮叶片气膜冷却孔直径对总冷却效率影响的实验研究
Q4 ENGINEERING, MECHANICAL Pub Date : 2023-06-30 DOI: 10.33737/jgpps/165825
Dogan Bicat, Katharina Stichling, Maximilian Elfner, Hans-Jörg Bauer, Knut Lehmann
Cyclone cooling is a promising method for a more effective internal cooling of turbine rotor blades with simplified internal channels including a swirling flow to enhance internal heat transfer. Previous studies have led to the conclusion that improving the cooling performance requires an adapted film cooling design, tailored to the cyclone cooling application. In this paper, a turbine rotor blade with realistic, complex features including the cyclone cooling design is investigated experimentally using infrared thermography to capture surface temperature. The objective is to analyze the influence of increased film cooling hole diameter on a cyclone-cooled blade’s surface temperature. For this purpose, the diameter of the holes at the blade’s leading edge, which are fed by the cyclone channel, is increased. The tests are performed for different coolant mass flow rates and swirl numbers. Additionally, CFD simulations are performed to analyze the aerodynamics of the cooling air. The test results show that the surface temperature at the leading edge can be decreased by increasing the diameter of the film cooling holes, however, adversely affecting the remaining blade surface. This can be explained by a redistribution of the supplied coolant. The increase of cooling effectiveness at the leading edge is at the highest when a low swirl is generated.
旋风冷却是一种有前途的更有效的涡轮转子叶片内部冷却方法,它简化了内部通道,包括旋涡流,以增强内部传热。以前的研究已经得出结论,提高冷却性能需要一个适应的膜冷却设计,量身定制的旋风冷却应用。本文利用红外热成像技术对具有旋风冷却设计等现实复杂特征的涡轮转子叶片表面温度进行了研究。目的是分析增大气膜冷却孔直径对旋风冷却叶片表面温度的影响。为此,增加了叶片前缘由旋风通道供给的孔的直径。在不同的冷却剂质量流量和旋流数下进行了试验。此外,还进行了CFD模拟,分析了冷却空气的空气动力学特性。试验结果表明,增大气膜冷却孔的直径可以降低叶片前缘的表面温度,但对叶片剩余表面的温度有不利影响。这可以用重新分配供给的冷却剂来解释。当产生低涡流时,前缘冷却效率的提高幅度最大。
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引用次数: 0
Systematic roughness variation to model the influence of skewness on wall bounded flows 系统的粗糙度变化来模拟偏度对壁面有界流动的影响
IF 0.9 Q4 ENGINEERING, MECHANICAL Pub Date : 2023-06-14 DOI: 10.33737/jgpps/163089
Sebastian Kurth, Cengiz Kenan, Moeller Daniel, Wein Lars, J. Seume
In recent years, the research on roughness has focused on various roughness features, rather than the roughness height only, in order to improve the understanding of roughness effects on wall bounded flows. A special focus is placed on the skewness of the roughness height profile. The skewness measures whether the height profile is dominated by negative or positive roughness elements. Surfaces with both features can be found on worn blades: On the leading edge, roughness is caused by the impact of particles resulting in a negative skewness. Rough surfaces around the trailing edge, however, develop due to depositions leading to a positive skewness.In this paper, rough surfaces taken from a compressor blade of an aero engine are systematically varied to investigate the isolated effect of skewness on aerodynamic losses. By direct numerical simulations of a periodic flow channel. The results show that the skewness has a major influence on loss generation. Based on these results, an existing model which essentially uses the shape-and-density parameter, is extended by a skewness factor. The modified correlation predicts the influence of the rough surfaces investigated well.
近年来,对粗糙度的研究集中在各种粗糙度特征上,而不仅仅是粗糙度高度,以提高对粗糙度对壁面有界流影响的理解。特别关注粗糙度高度轮廓的倾斜度。偏斜度测量高度轮廓是由负粗糙度元素还是正粗糙度元素主导。在磨损的叶片上可以找到具有这两种特征的表面:在前缘,粗糙度是由颗粒的影响引起的,从而导致负偏斜。然而,后缘周围的粗糙表面由于沉积物而形成,从而导致正偏斜度。本文系统地改变了航空发动机压气机叶片的粗糙表面,以研究偏斜度对气动损失的孤立影响。通过对周期性流道的直接数值模拟。结果表明,偏度对损失的产生有重要影响。基于这些结果,通过偏斜度因子对基本上使用形状和密度参数的现有模型进行了扩展。修正后的相关性很好地预测了所研究的粗糙表面的影响。
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引用次数: 0
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Journal of the Global Power and Propulsion Society
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