International Journal of Turbomachinery, Propulsion and Power最新文献_第3页

An Experimental Database for the Analysis of Bursting of a Laminar Separation Bubble 分析层流分离气泡破裂的实验数据库

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2024-01-10 DOI: 10.3390/ijtpp9010003

M. Dellacasagrande, D. Lengani, D. Simoni, M. Ubaldi

{"title":"An Experimental Database for the Analysis of Bursting of a Laminar Separation Bubble","authors":"M. Dellacasagrande, D. Lengani, D. Simoni, M. Ubaldi","doi":"10.3390/ijtpp9010003","DOIUrl":"https://doi.org/10.3390/ijtpp9010003","url":null,"abstract":"The bursting phenomenon consists in the switch of a laminar separation bubble from a short to a long configuration. In the former case, reduced effects on profile pressure distribution are typically observed with respect to the attached condition. On the contrary, long bubbles provoke significant variations in the loading coefficient upstream of the separation position, with increased risk of stall of the lifting surfaces. The present work presents an experimental database describing separated boundary layers evolving under different Reynolds numbers, adverse pressure gradients and free-stream turbulence levels. Overall, more than 80 flow conditions were tested concerning short and long bubbles for the characterization of separated flows under turbine-like conditions. Measurements were performed on a flat plate geometry using a fast-response Particle Image Velocimetry (PIV) system. For each flow case, two sets of 6000 flow records were acquired with an acquisition frequency equal to 300 and 1000 Hz. Based on existing criteria for the identification of the bursting phenomenon, the flow cases were clustered in terms of short and long bubble states. Additionally, the kind of instability (i.e., convective or absolute) developing into the separated boundary layer was identified based on flow statistics. The present data captures the existing link between the bursting of a laminar separation bubble and the onset of the absolute instability of the separated shear layer, with stationary vortices forming in the dead air region.","PeriodicalId":36626,"journal":{"name":"International Journal of Turbomachinery, Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2024-01-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139441157","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Effect of Leading-Edge Erosion on the Performance of Transonic Compressor Blades 前缘腐蚀对跨音速压缩机叶片性能的影响

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2024-01-09 DOI: 10.3390/ijtpp9010001

A. Hergt, Tobias Danninger, J. Klinner, S. Grund, M. Beversdorff, C. Werner-Spatz

引用次数: 0

Comparison Study of the k − kL − ω and γ − Reθ Transition Model in the Open-Water Performance Prediction of a Rim-Driven Thruster 轮缘驱动推进器开阔水域性能预测中 k - kL - ω 和 γ - Reθ 过渡模型的比较研究

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2024-01-09 DOI: 10.3390/ijtpp9010002

Bao Liu, M. Vanierschot, F. Buysschaert

{"title":"Comparison Study of the k − kL − ω and γ − Reθ Transition Model in the Open-Water Performance Prediction of a Rim-Driven Thruster","authors":"Bao Liu, M. Vanierschot, F. Buysschaert","doi":"10.3390/ijtpp9010002","DOIUrl":"https://doi.org/10.3390/ijtpp9010002","url":null,"abstract":"The present work examines the capabilities of two transition models implemented in ANSYS Fluent in the open-water performance prediction of a rim-driven thruster (RDT). The adopted models are the three-equation k−kL−ω and the four-equation γ−Reθ models. Both of them are firstly tested on a ducted propeller. The numerical results are compared with available experimental data, and a good correlation is found for both models. The simulations employing two transition models are then carried out on a four-bladed rim-driven thruster model and the results are compared with the SST k−ω turbulence model. It is observed that the streamline patterns on the blade surface are significantly different between the transition and fully turbulent models. The transition models can reveal the laminar region on the blade while the fully turbulent model assumes the boundary layer is entirely turbulent, resulting in a considerable difference in torque prediction. It is noted that unlike the fully turbulent model, the transition models are quite sensitive to the free-stream turbulence quantities such as turbulent intensity and turbulent viscosity ratio, as these quantities determine the onset of the transition process. The open-water performance of the studied RDT and resolved flow field are also presented and discussed.","PeriodicalId":36626,"journal":{"name":"International Journal of Turbomachinery, Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2024-01-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139443085","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

A Comparison of Steam Turbine Control Valve Geometries and Their Dynamic Behavior at Part Load 蒸汽轮机控制阀几何形状及其部分负荷下的动态行为比较

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-12-18 DOI: 10.3390/ijtpp8040055

Christian Windemuth, M. Lange, Ronald Mailach

引用次数: 0

NREL-5MW Wind Turbine Noise Prediction by FWH-LES 通过 FWH-LES 预测 NREL-5MW 风机噪声

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-12-06 DOI: 10.3390/ijtpp8040054

Claudio Bernardi, F. Porcacchia, Claudio Testa, P. De Palma, Stefano Leonardi, S. Cherubini

引用次数: 0

Numerical Modelling of the 3D Unsteady Flow of an Inlet Particle Separator for Turboshaft Engines 涡轮轴发动机进气颗粒分离器的三维非稳态流动数值建模

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-12-04 DOI: 10.3390/ijtpp8040052

Marco Castaldi, Ignacio Mayo, Jacques Demolis, Frank Eulitz

引用次数: 0

Fan Stage Design and Performance Optimization for Low Specific Thrust Turbofans 低比推力涡轮风扇的风扇级设计和性能优化

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-12-04 DOI: 10.3390/ijtpp8040053

Oliver Sjögren, T. Grönstedt, A. Lundbladh, C. Xisto

{"title":"Fan Stage Design and Performance Optimization for Low Specific Thrust Turbofans","authors":"Oliver Sjögren, T. Grönstedt, A. Lundbladh, C. Xisto","doi":"10.3390/ijtpp8040053","DOIUrl":"https://doi.org/10.3390/ijtpp8040053","url":null,"abstract":"In modern turbofan engines, the bypass section of the fan stage alone provides the majority of the total thrust required in cruise, and the size of the fan has a considerable effect on the overall engine weight and nacelle drag. Thrust requirements in different parts of the flight envelope must also be satisfied together with sufficient margins towards stalling. An accurate description of the interdependencies between the relevant performance and design attributes of the fan stage alone—such as efficiency, surge margin, fan-face Mach number, stage loading, flow coefficient, and aspect ratio—are therefore necessary to estimate system-level objectives such as mission fuel burn and the direct operating cost with enough confidence during the conceptual design phase. The contribution of this study is to apply a parametric optimization approach to the conceptual design of fan stages for low specific thrust turbofans based on the streamline curvature method. Trade-offs between fan stage attributes for Pareto-optimal solutions are modeled by training Kriging surrogate models on the results from the parametric optimization. A case study is provided in the end to demonstrate the potential implications of including a higher level of fan-stage parameter interdependency in an engine systems model. Results implied that being able to predict the rotor solidity required to maintain a given average blade loading—in addition to stage efficiency—is of significant importance when it comes to evaluating the trade-off between engine weight and thrust-specific fuel consumption.","PeriodicalId":36626,"journal":{"name":"International Journal of Turbomachinery, Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2023-12-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138601536","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Effect of Porosity and Injection Ratio on the Performance of Transpiration Cooling through Gyroids 孔隙率和喷射比对通过陀螺仪进行蒸气冷却的性能的影响

IF 1.4

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-12-01 DOI: 10.3390/ijtpp8040050

Benjamin J. Brimacombe, James A. Scobie, Joseph M. Flynn, C. Sangan, Oliver J Pountney

引用次数: 0

Determination of a Numerical Surge Limit by Means of an Enhanced Greitzer Compressor Model 用增强型Greitzer压缩机模型确定喘振数值极限

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-11-14 DOI: 10.3390/ijtpp8040048

Tobias Haeckel, Dominik Paul, Sebastian Leichtfuß, Heinz-Peter Schiffer, Werner Eißler

{"title":"Determination of a Numerical Surge Limit by Means of an Enhanced Greitzer Compressor Model","authors":"Tobias Haeckel, Dominik Paul, Sebastian Leichtfuß, Heinz-Peter Schiffer, Werner Eißler","doi":"10.3390/ijtpp8040048","DOIUrl":"https://doi.org/10.3390/ijtpp8040048","url":null,"abstract":"The surge limit of centrifugal compressors is a key parameter in the design process of modern turbochargers. Numerical methods like steady-state simulations are state-of-the-art methods for predicting the performance of the centrifugal compressor. In contrast to that, the determination of the surge limit with any numerical method is still an unsolved challenge. Since the extensive work of Greitzer and many other researchers in this field, it is well-known that surge is a system-dependent phenomenon. In the case of steady-state simulations, the simulation domain is chosen to be as small as possible due to the numerical cost. This simply implies that there is no system information included in the numerical model. Therefore, it is not possible to determine any system-dependent surge limit with today’s applied numerical methods. To overcome this issue, an enhanced Greitzer surge model, which has been developed at Tu Darmstadt, should act as a link between the simulation and the system in which the compressor will be operated. The focus of this paper will rather be on the methodology of determining the surge limit by means of numerical data than on the surge model itself. The methodology will be validated by experimental data of different systems.","PeriodicalId":36626,"journal":{"name":"International Journal of Turbomachinery, Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134992174","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

The Current Gap between Design Optimization and Experiments for Transonic Compressor Blades 跨声速压气机叶片设计优化与实验之间的差距

International Journal of Turbomachinery, Propulsion and Power Pub Date : 2023-11-13 DOI: 10.3390/ijtpp8040047

Edwin Joseph Munoz Lopez, Alexander Hergt, Till Ockenfels, Sebastian Grund, Volker Gümmer

引用次数: 0