Journal of Turbomachinery-Transactions of the Asme最新文献_第7页

Internal Heat Transfer Measurement on Metal-Based Additively Manufactured Channels Using a Transient Technique 用瞬态技术测量金属基增材制造通道的内部传热

3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-07-27 DOI: 10.1115/1.4062807

Patrick Lüscher, Marin Deflorin, Manuel Voggesser, Peter Stuber, Vincent Galoul, Minseok Ko

{"title":"Internal Heat Transfer Measurement on Metal-Based Additively Manufactured Channels Using a Transient Technique","authors":"Patrick Lüscher, Marin Deflorin, Manuel Voggesser, Peter Stuber, Vincent Galoul, Minseok Ko","doi":"10.1115/1.4062807","DOIUrl":"https://doi.org/10.1115/1.4062807","url":null,"abstract":"Abstract The advancements in additive manufacturing (AM) of metals open new possibilities in the design of gas turbine parts. Especially the cooling efficiency of internal channels can be improved with more complex geometries. Naturally, AM channels have a higher surface roughness than conventionally manufactured parts, which influences the cooling air pressure loss as well as the heat transfer. Implementing novel cooling designs using AM can be possible only if the effect of increased surface roughness on the flow and on the heat transfer can be predicted with an appropriate accuracy. The objective of the current study was to measure these parameters experimentally in simple AM channels to build a database for designing complex and efficient cooling designs using the AM technique. A test rig and postprocessing method was elaborated to derive the local internal heat transfer distribution of metal-based AM channels. Six circular single channel coupons made by selective laser melting (SLM) were tested for Reynolds numbers ranging from 20,000 to 50,000. The coupon with the lowest relative roughness shows good agreement with the Dittus–Boelter correlation. All the other coupons show a consistent increase of internal heat transfer and flow friction with the increase of the internal surface roughness.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-07-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135656934","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Excitation of a Separated Flow by a Series of Protuberances near the Leading Edge of a Model Aerofoil 模型翼型前缘附近一系列凸起对分离流的激励

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-07-25 DOI: 10.1115/1.4063048

Pradeep Singh, Subrata Sarkar

{"title":"Excitation of a Separated Flow by a Series of Protuberances near the Leading Edge of a Model Aerofoil","authors":"Pradeep Singh, Subrata Sarkar","doi":"10.1115/1.4063048","DOIUrl":"https://doi.org/10.1115/1.4063048","url":null,"abstract":"\u0000 The paper documents the manifestation of a shear layer under the excitation of a series of hemispherical protuberances near the leading edge of a constant-thickness airfoil. The experiments are performed at a Reynolds number of 1.6 × 105 based on the chord length and inlet velocity, where freestream turbulence is 1.2%. The hotwire and particle image velocimetry data are analyzed to appreciate the flow feature, illustrating the growth of perturbations, vortex dynamics, intermittency, and spectral response. A laminar separation bubble (LSB) appears near the leading edge for a smooth surface, and the shear layer is inviscidly unstable. The evolution of the shear layer significantly changes with a series of protuberances. The breakdown of the shear layer occurs almost immediately, triggering local turbulence resulting in a considerable reduction of bubble length. A separation bubble, which is highly asymmetric in the spanwise direction, is formed in this case. Although the power spectra of velocity fluctuations reveal the selective amplification of frequencies even with protuberances, the immediate augmentation of turbulence followed by faster decay suggests the transient growth of turbulence. The study has documented insight into features of a separation bubble subjected to leading-edge perturbations and might influence future studies on separation control over an airfoil.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-07-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47943459","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Film Cooling on Turbine Vane Endwalls with Different Inlet Cooling Configurations: Experimental and Computational Results 不同进口冷却结构涡轮叶片端壁的气膜冷却:实验与计算结果

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-07-25 DOI: 10.1115/1.4063050

Xing Yang, Qiang Zhao, Hang Wu, Z. Feng

{"title":"Film Cooling on Turbine Vane Endwalls with Different Inlet Cooling Configurations: Experimental and Computational Results","authors":"Xing Yang, Qiang Zhao, Hang Wu, Z. Feng","doi":"10.1115/1.4063050","DOIUrl":"https://doi.org/10.1115/1.4063050","url":null,"abstract":"\u0000 A comparative study of turbine endwall film cooling resulting from three different cooling configurations in front of the passage inlet was conducted. The three inlet cooling configurations investigated in this study were a conventional continuous slot, double rows of discrete film holes, and an interrupted slot with a backward-facing step. Pressure Sensitive Paint (PSP) was sprayed over the endwall surfaces to map cooling effectiveness contours and five-hole probe and thermocouple measurements were implemented to assess aero-thermal fields at the passage exit. The evolution of cooling effectiveness is compared across a full range span of coolant flow rates of 0.3%-1.8% in a real engine. Additionally, complex flow structures inside the passage due to interactions of coolant with mainstream flows were visualized using Computational Fluid Dynamics (CFD) simulations to support the observed coolant coverage patterns. The continuous slot was found to produce the highest cooling effectiveness values while the double-row holes offered the most uniform coolant coverage, leading to spreading out of the coolant jets downstream of the passage throat and even beyond the trailing edge of the passage for coolant injection rates higher than 1.0%. Supported by the CFD-predicted flow structures and measured aerodynamic losses, the injection from the double-row holes weakened the passage secondary flows and thus caused the lowest aerodynamic loss. On the contrary, the interrupted slot enhanced the secondary flows due to the backward step, resulting in the highest flow loss.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-07-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44948497","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Using data assimilation to improve turbulence modeling for inclined jets in crossflow 利用数据同化改进横流中倾斜射流的湍流建模

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-07-25 DOI: 10.1115/1.4063047

Xu Zhang, Kechen Wang, Wenwu Zhou, Chuangxin He, Yingzheng Liu

{"title":"Using data assimilation to improve turbulence modeling for inclined jets in crossflow","authors":"Xu Zhang, Kechen Wang, Wenwu Zhou, Chuangxin He, Yingzheng Liu","doi":"10.1115/1.4063047","DOIUrl":"https://doi.org/10.1115/1.4063047","url":null,"abstract":"\u0000 Data assimilation (DA) integrating limited experimental data and computational fluid dynamics is applied to improve the prediction accuracy of flow and mixing behavior in inclined jet-in-crossflow (JICF). The ensemble Kalman filter (EnKF) approach is used as the DA technique, and the Reynolds-averaged Navier-Stokes (RANS) modeling serves as the prediction framework. The flow field and scalar mixing characteristics of a cylinder inclined JICF and a sand dune (SD) -inspired inclined JICF are studied at various velocity ratios (VR = 0.4, 0.8, and 1.2). Firstly, the Spalart-Allmaras (SA) model and the standard k-e model are investigated based on the cylinder configuration at VR = 1.2. An optimized set of model constants are determined for each model using the EnKF-based data assimilation. The SA model shows remarkable improvement and better prediction in flow separation than the standard k-e model after DA. Further exploration demonstrates that this set of SA model constants can be extended to other VRs and even the SD-inspired configuration, mainly due to the correction of the predicted flow separation in inclined JICF. Finally, an investigation of the concentration field also shows satisfying improvement, resulting from a more appropriate turbulent Schmidt number. The optimized model constants, the revealed extensibility, and the uncovered mechanism of using the EnKF-based DA to improve the simulation of JICF could facilitate the design of related applications such as gas turbine film cooling.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-07-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48449062","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Body Force Modeling of the Fan Stage of a Windmilling Turbofan 某型风力涡轮风扇扇级体力建模

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-06-26 DOI: 10.1115/1.4062837

M. Lagha, G. Dufour

{"title":"Body Force Modeling of the Fan Stage of a Windmilling Turbofan","authors":"M. Lagha, G. Dufour","doi":"10.1115/1.4062837","DOIUrl":"https://doi.org/10.1115/1.4062837","url":null,"abstract":"\u0000 The determination of the rotational speed and massflow of the fan of a turbofan at windmill is critical in the design of the engine-supporting structure and the sizing of the vertical stabilizer. Given the very high bypass ratio obtained at windmill, the flow in the fan stage and bypass duct is of prime interest. Classical CFD simulations have been shown to predict such flows accurately, but extensive parametric studies can be needed, stressing the need for reduced-cost modeling of the flow in the engine. A Body Force Modeling (BFM) approach for windmilling simulations is examined in the present contribution. The BFM approach replaces turbomachinery rows by source terms, reducing the computational cost (here by a factor 5). A shaft model is coupled to the BFM source terms, to drive the simulation to a power balance of the low-pressure shaft. The overall approach is thus self-contained and can predict both the massflow and the rotational speed in the windmilling regime. Comparisons with engine experimental results show the proposed model can predict the rotational speed within 7 %, and the massflow within 5 %. Local analysis and comparisons with experimental data and reference blade calculations show that the work exchange, in term of total temperature variation, is predicted within 0.5 K, and the overall total pressure ratio within 1 %. However, the losses in the stator are largely underestimated, which explains the discrepancy for the massflow predictions.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42601998","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Hot-Wire Anemometry in High Subsonic Organic Vapor Flows 高亚音速有机蒸汽流中的热线风速测定

3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-06-26 DOI: 10.1115/1.4062676

Leander Hake, Stefan aus der Wiesche, Stephan Sundermeier, Leon Cakievski, Joshua Bäumer, Paola Cinnella, Camille Matar, Xavier Gloerfelt

引用次数: 1

Characterizing Shrouded Stator Cavity Flow on the Performance of a Single-Stage Axial Transonic Compressor 带罩定子腔流对单级轴流跨音速压缩机性能的影响

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-06-26 DOI: 10.1115/1.4063296

Runzhu Shao, Xiao He, Mingmin Zhu, Fabian Klausmann, Jinfang Teng

{"title":"Characterizing Shrouded Stator Cavity Flow on the Performance of a Single-Stage Axial Transonic Compressor","authors":"Runzhu Shao, Xiao He, Mingmin Zhu, Fabian Klausmann, Jinfang Teng","doi":"10.1115/1.4063296","DOIUrl":"https://doi.org/10.1115/1.4063296","url":null,"abstract":"\u0000 Shrouded stator cavity flow increases the stator total pressure loss, reduces the compressor isentropic efficiency and thus limits the compressor pressure rise capability. This paper proposes a simplified cavity flow model that consists of flow injection at the stator inlet and flow suction at the stator outlet. Based on this model, a full-factorial parametric study on the leakage flow ratio and the leakage swirl angle is performed at different rotational speeds and incidences. In the first place, the effectiveness of the numerical method is validated against the experimental data based on the full-scale cavity geometry; then, the numerical simulations on the simplified cavity geometry are validated against that of the full-scale one. Results show that the leakage flow ratio plays a dominant role in determining the compressor performance penalty. The isentropic efficiency drops almost linearly with the leakage flow ratio due to deteriorated near-hub separations, and the slope becomes steeper at higher operating speeds and incidences. The leakage swirl angle only has a pronounced effect under a high leakage flow ratio. The efficiency penalty reduces with increasing swirl angle due to an alleviated tangential flow mixing and suppressed near-hub separations. The swirl angle effect is more pronounced at lower incidence conditions. These findings advance the fundamental understanding of shrouded stator cavity flow effects and provide useful guidance for cavity seal designs.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49613074","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

HIGH-FIDELITY COMPUTATIONAL ASSESSMENT OF AERO-THERMAL PERFORMANCE AND THE REYNOLDS' ANALOGY FOR ADDITIVELY MANUFACTURED ANISOTROPIC SURFACE ROUGHNESS 气-热性能的高保真度计算评估及添加制造的各向异性表面粗糙度的雷诺模拟

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-06-26 DOI: 10.1115/1.4063298

T. Jelly, W. Abu Rowin, N. Hutchins, D. Chung, Koichi Tanimoto, Takuo Oda, R. Sandberg

{"title":"HIGH-FIDELITY COMPUTATIONAL ASSESSMENT OF AERO-THERMAL PERFORMANCE AND THE REYNOLDS' ANALOGY FOR ADDITIVELY MANUFACTURED ANISOTROPIC SURFACE ROUGHNESS","authors":"T. Jelly, W. Abu Rowin, N. Hutchins, D. Chung, Koichi Tanimoto, Takuo Oda, R. Sandberg","doi":"10.1115/1.4063298","DOIUrl":"https://doi.org/10.1115/1.4063298","url":null,"abstract":"\u0000 Direct numerical simulations of incompressible turbulent forced convection over irregular, anisotropic surface roughness in a pressure-driven plane channel flow have been performed. Heat transfer was simulated by solving the passive scalar transport equation with Prandtl number Pr = 0.7. The roughness topographies under investigation here are based on an X-ray computed tomography scan of an additively manufactured internal cooling passage, which had an irregular, multi-scale and mildly non-Gaussian height distribution. Three different roughness topographies and three different friction Reynolds numbers (Reτ = 395, 590, 720) were considered, along with reference smooth-wall simulations at matched Reτ. By systematically varying the roughness topography and flow conditions, a direct computational assessment of aero-thermal performance (pressure losses and heat transfer) and the Reynolds analogy factor, i.e. 2Ch/Cf, where Ch is the heat-transfer coefficient (Stanton number) and Cf is the skin-friction coefficient, was conducted. The results highlight the profound impact that the roughness orientation (relative to the flow direction) has upon the aero-thermal performance of additively manufactured internal passages, with transverse-aligned roughness augmenting heat transfer by as much as 33%, relative to its streamwise-aligned counterpart. An interrogation of velocity and temperature statistics in the near- wall region was also performed, which underlined the growing dissimilarity between heat transfer and drag as fully-rough conditions are approached.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43334741","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Fan Flutter Mechanisms Related to Blade Mode Shape and Acoustic Properties 与叶片模态形状和声学特性相关的风扇颤振机理

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-06-21 DOI: 10.1115/1.4062806

Xu Dong, Yanfeng Zhang, Xin'gen Lu

{"title":"Fan Flutter Mechanisms Related to Blade Mode Shape and Acoustic Properties","authors":"Xu Dong, Yanfeng Zhang, Xin'gen Lu","doi":"10.1115/1.4062806","DOIUrl":"https://doi.org/10.1115/1.4062806","url":null,"abstract":"\u0000 The blade mode shape and acoustic properties are important factors that affect the aeroelasticity of fan blades. The goal of this paper is to investigate the stall flutter mechanism associated with the first mode and its components. The paper numerically studies the impact of blade modes on fan flutter under different acoustic propagation conditions. The research focus includes unsteady characteristics inside blade passages, variations in pressure waves under different acoustic modes, as well as the effects of blade modes on the least stable phase angle. The results show that the twist-induced pressure leads to destabilization. Compared with the work of other authors, this study discovered that when the twist-induced pressure on the pressure side act on the plunge rather than twist, the instability effect will be greater, while the effect of twist-induced pressure on suction side is weak. The phase of unsteady pressure in two-dimensional flow regions is linear with frequency, while the amplitude is highly sensitive to acoustic properties. The plunge-induced pressure inside the passage undergoes significant changes when downstream is from acoustic cut-off to cut-on. The twist-induced pressure is more sensitive to changes in the acoustic propagation state, with the peak of the aerodynamic damping curve near upstream acoustic resonance being solely related to the twist-induced pressure acting on the suction side. The study also finds that the position of the blade torsion axis, represented by the twist-to-plunge ratio, does not affect the most unstable nodal diameter.","PeriodicalId":49966,"journal":{"name":"Journal of Turbomachinery-Transactions of the Asme","volume":" ","pages":""},"PeriodicalIF":1.7,"publicationDate":"2023-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42407586","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

An Aerodynamic Loss Model for Axial Turbine Design 轴流式水轮机设计的气动损失模型

IF 1.7 3区工程技术

Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-06-21 DOI: 10.1115/1.4062804

Zhi Li, Liu Yan

引用次数: 0