Journal of the Global Power and Propulsion Society最新文献_第3页

Validation and verification of RANS solvers for TUDa-GLR-OpenStage transonic axial compressor tada - glr - openstage跨声速轴流压气机RANS求解器的验证与验证

Journal of the Global Power and Propulsion Society Pub Date : 2023-01-27 DOI: 10.33737/jgpps/158034

Xiao He, Mingmin Zhu, Kailong Xia, Klausmann Fabian, Jinfang Teng, Mehdi Vahdati

{"title":"Validation and verification of RANS solvers for TUDa-GLR-OpenStage transonic axial compressor","authors":"Xiao He, Mingmin Zhu, Kailong Xia, Klausmann Fabian, Jinfang Teng, Mehdi Vahdati","doi":"10.33737/jgpps/158034","DOIUrl":"https://doi.org/10.33737/jgpps/158034","url":null,"abstract":"This paper presents a comprehensive validation and verification study of turbomachinery Reynolds-averaged Navier-Stokes flow solvers on the transonic axial compressor TUDa-GLR-OpenStage. Two commercial solvers namely Ansys CFX and Numeca FineTurbo are adopted to provide the benchmark solutions, which can be used for verification of other RANS solvers in the future. Based on these solvers, five sets of grids, two advection schemes (i.e., central difference and second-order upwind), four turbulence models (i.e., SA, SA-RC, SST and EARSM) and two rotor-stator interface models (i.e., mixing plane and sliding plane) are investigated to quantify their effects on predicting the performance and the flow field of the compressor stage. Results show that the choices of grid density and turbulence model are most sensitive to the prediction, leading to 5% and 7% variation in compressor performance characteristics, respectively. Regarding the choice of grid density, a method to estimate the grid discretization error is demonstrated, which is transferrable to other cases. Regarding the choice of turbulence model, the EARSM model is found overall most accurate among the investigated models, and the limitations and deficiencies of the rest models are discussed in detail based on the analysis of the mean flow fields and the eddy viscosity fields. The grids and the major CFD results presented in this work are open-accessed to the community for further research. The results and discussions presented in this paper provide a useful reference for future practices of RANS simulations for compressors.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":"671 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135743532","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: 5

Numerical investigations on the unsteady leakage flow and heat transfer characteristics of the turbine blade squealer tip 涡轮叶片尖部非定常泄漏流动及换热特性数值研究

Journal of the Global Power and Propulsion Society Pub Date : 2023-01-05 DOI: 10.33737/jgpps/157176

Shijie Jiang, Zhigang Li, Jun Li, Liming Song

{"title":"Numerical investigations on the unsteady leakage flow and heat transfer characteristics of the turbine blade squealer tip","authors":"Shijie Jiang, Zhigang Li, Jun Li, Liming Song","doi":"10.33737/jgpps/157176","DOIUrl":"https://doi.org/10.33737/jgpps/157176","url":null,"abstract":"The unsteady leakage flow and heat transfer characteristics of the turbine blade squealer tip was numerically investigated using three-dimensional Unsteady Reynolds-Averaged Naiver-Stokes (URANS) and standard k-ω turbulence model. The numerical simulated heat transfer coefficients of the turbine blade tip were well agreement with the experimental data. The accuracy of the numerical method was validated. The steady and unsteady leakage flow and heat transfer coefficient of the turbine blade squealer tip with and without film cooling was conducted. The unsteady leakage flow and heat transfer characteristics of the turbine blade squealer tip with film cooling design at three different blow ratios was numerically investigated. The obtained results show that the corner vortex and scraping vortex near the pressure side shows periodic fluctuation along the separation line of the leakage flow under the function of the pressure difference between the suction and pressure side of the blade tip, as well as the upstream vane unsteady wake flow. This unsteady flow behavior results in the fluctuation of the high heat transfer coefficients at the blade tip. The film cooling design along the camber line can effectively reduce the thermal load of the turbine blade squealer tip by comparison to without film cooling case. The time-averaged heat transfer coefficients of the turbine blade squealer tip reduce 9.0%, 12.4% and 13.2% at blowing ratio of .0.5, 1.0 and 1.5 comparison to without film cooling design in respective. The present work can provide the reference of the film cooling design for the turbine blade squealer tip.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135323557","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

Investigation of coupled radiation-conduction heat transfer in cylindrical systems by discontinuous spectral element method 用不连续谱元法研究圆柱形系统中耦合辐射-传导传热

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Journal of the Global Power and Propulsion Society Pub Date : 2022-12-30 DOI: 10.33737/jgpps/156350

Jiazi Zhao, Yasong Sun, Yifang Li, Changhao Liu

{"title":"Investigation of coupled radiation-conduction heat transfer in cylindrical systems by discontinuous spectral element method","authors":"Jiazi Zhao, Yasong Sun, Yifang Li, Changhao Liu","doi":"10.33737/jgpps/156350","DOIUrl":"https://doi.org/10.33737/jgpps/156350","url":null,"abstract":"Nowadays, in order to achieve higher efficiency in aero-engines, the increase of turbine inlet temperature in aero-engine is in urgent need. At present, the turbine inlet temperature is around 2,000 K, which means the radiation and coupled radiation-conduction heat transfer play more and more important roles in hot section of aero-engines. As we all konw, considering the cylindrical symmetry of aero-engines. It is convenient to adopt the cylindrical coordinate to simplify the description of these systems, such as annular combustor, exhaust nozzle, etc. In this paper, Discontinuous Spectral Element Method (DSEM) is extended to solve the radiation and coupled radiation-coduction heat transfer in cylindrical coordinate system. Both the spatial and angular computational domains of radiative transfer equation (RTE) are discretized and solved by DSEM. For coupled radiation-conduction heat transfer problem, Discontinuous Spectral Element Method-Spectral Element Method (DSEM-SEM) scheme is used to avoid using two sets of grid which would cause the increase of computational cost and the decrease of accuracy. Then, the effects of various geometric and thermal physical parameters are comprehensively investigated. Finally, these methods are further extended to 2D cylindrical system.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-12-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41970774","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

Effects of scaling laws on flow and combustion characteristics of lean premixed swirl burners 比例缩放规律对稀薄预混旋流燃烧器流动和燃烧特性的影响

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Journal of the Global Power and Propulsion Society Pub Date : 2022-12-20 DOI: 10.33737/jgpps/156121

Wenda Xie, Ting Shi, B. Ge, S. Zang

引用次数: 2

LES prediction of transitional flows in LP turbine cascades: effects of blade loading, flow phenomena and numerical setup 低压涡轮叶栅过渡流动的LES预测:叶片载荷、流动现象和数值设置的影响

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Journal of the Global Power and Propulsion Society Pub Date : 2022-12-20 DOI: 10.33737/jgpps/156577

A. Tateishi, N. Tani, Y. Okamura, Masaaki Hamabe

{"title":"LES prediction of transitional flows in LP turbine cascades: effects of blade loading, flow phenomena and numerical setup","authors":"A. Tateishi, N. Tani, Y. Okamura, Masaaki Hamabe","doi":"10.33737/jgpps/156577","DOIUrl":"https://doi.org/10.33737/jgpps/156577","url":null,"abstract":"This paper presents detailed validations of a Large Eddy Simulation (LES) methodology for various transitional phenomena in low pressure turbines. The results are discussed to identify key phenomena to be resolved accurately toward future industrial use of LES. Detailed comparisons between experimental and CFD results are made on three different 2D cascades with different blade loading. One is low-lift and fully laminar design, while the others are moderate- and high-lift designs with boundary layer transition. The experimental data are obtained in a low speed linear cascade at Iwate University. All computations are conducted by a carefully-designed overset LES code. For the high-load design with a distinct laminar separation on the suction side, the LES result shows satisfactory agreement with the test. However, although the peak of total pressure loss distribution is predicted quite accurately, integrated cascade losses are over-predicted in the other two cases. For the laminar blade, the LES result implies some differences can exist in the state of wake, while the transitional blade shows delay of transition in the boundary layer. The effects of inflow turbulence intensity, length scale, and stream tube contraction are discussed in detail to improve LES prediction.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-12-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42926492","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

Transonic compressor Darmstadt - Open test caseIntroduction of the TUDa open test case 跨音速压缩机Darmstadt -开放式测试用例TUDa开放式测试用例介绍

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Journal of the Global Power and Propulsion Society Pub Date : 2022-12-12 DOI: 10.33737/jgpps/156120

Fabian Klausmann, D. Franke, J. Foret, H. Schiffer

{"title":"Transonic compressor Darmstadt - Open test case\u0000\u0000Introduction of the TUDa open test case","authors":"Fabian Klausmann, D. Franke, J. Foret, H. Schiffer","doi":"10.33737/jgpps/156120","DOIUrl":"https://doi.org/10.33737/jgpps/156120","url":null,"abstract":"Designs for future aero engines aim for increased efficiency with reduced exhaust gas and noise emissions. To achieve these goals, comprehensive physical understanding and highly innovative solutions are necessary. Even though computational capabilities are rising, the required confidence level is restrained. To understand and validate theoretical and numerical models, extensive experiments at realistic operating conditions are crucial.\u0000\u0000The modular compressor at the Transonic Compressor Darmstadt test facility at Technical University of Darmstadt enables investigations of prototype BLISK rotors in single or 1.5-stage setups, operating at high-speed conditions. Extensive steady and time-resolving instrumentation is used to determine the compressor aerodynamics and performance as well as aeroelastics.\u0000\u0000To foster improvements in numerical modelling and predictability based on high quality experimental data, the TUDa-GLR-OpenStage test case is introduced. It comprises a single stage setup, including the BLISK rotor, a 3D-optimized stator as well as the annulus contour. The data set is supplemented with comprehensive measurement data at stage inlet and outlet as well as running tip clearances.\u0000\u0000This paper describes the open test case, related geometries, measurement procedures and corresponding experimental results, including steady state performance and unsteady aerodynamics. Ultimately, it is aiming to provide a standard case for future development of numerical models and comparable validation.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-12-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46765016","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: 3

Investigation of surge in a 1.5-stage transonic axial compressor 1.5级跨声速轴流压气机喘振特性研究

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Journal of the Global Power and Propulsion Society Pub Date : 2022-11-28 DOI: 10.33737/jgpps/156119

Silas Mütschard, J. Werner, C. Kunkel, Maximilian Karl, H. Schiffer, C. Biela, Sebastian Robens

{"title":"Investigation of surge in a 1.5-stage transonic axial compressor","authors":"Silas Mütschard, J. Werner, C. Kunkel, Maximilian Karl, H. Schiffer, C. Biela, Sebastian Robens","doi":"10.33737/jgpps/156119","DOIUrl":"https://doi.org/10.33737/jgpps/156119","url":null,"abstract":"In this paper we give insight into characteristics of a 1.5-stage transonic axial compressor rig with focus on surge during a stalled operating point. The new compressor rig at TU Darmstadt is representative for the front stage of an industrial gas turbine. Transient throttling maneuvers were conducted for multiple operating points during the first test campaign of the TCD 2 (Transonic Compressor Darmstadt 2), providing an extensive set of unsteady structural and aerodynamic data beyond the stability limit. Enhanced analytical methods allow detailed studies including aerodynamic spectral analysis as well as determination of propagation speed and size of disturbances. The results differ from observations at comparable test rigs, revealing an interesting manifestation of stall: In a wide range of the stability limit it shows a periodicity. The stall emerges and vanishes recurrently, causing strong oscillations of the pressure ratio. Additional unsteady measurements of the mass flow indicate a surge. Regarding the compressor map, this results in staggering operating points, showing a hysteresis. However, due to a rather small plenum and experience with a similar test rig the TCD 2 was not expected to surge. Comprehensive analyses are carried out to characterize this phenomenon.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-11-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47175215","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

Predicting the ignition sequences in a separated stratified swirling spray flame with stochastic flame particle tracking 用随机火焰粒子跟踪方法预测分层旋转喷射火焰的点火顺序

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Journal of the Global Power and Propulsion Society Pub Date : 2022-10-12 DOI: 10.33737/jgpps/153495

Qing Xie, Siheng Yang, Hao Cheng, Chi Zhang, Zhuyin Ren

{"title":"Predicting the ignition sequences in a separated stratified swirling spray flame with stochastic flame particle tracking","authors":"Qing Xie, Siheng Yang, Hao Cheng, Chi Zhang, Zhuyin Ren","doi":"10.33737/jgpps/153495","DOIUrl":"https://doi.org/10.33737/jgpps/153495","url":null,"abstract":"Stochastic flame particle tracking in conjunction with non-reacting combustor simulations can offer insights into the ignition processes and facilitate the combustor optimization. In this study, this approach is employed to simulate the ignition sequences in a separated dual-swirl spray flame, in which the newly proposed pairwise mixing-reaction model is used to account for the mass and energy transfer between the flame particle and the surrounding shell layer. Based on the flame particle temperature, the particle state can be classified in to burnt, hot gas, and extinguished. The additional state of hot gas is introduced to allow the flame particles with high temperature to survive from nonflammable region and then potentially to ignite the nearby favourable regions. The simulations of the separated stratified swirl spray flame reveal two different ignition pathways for flame stabilization. The first showed that some flame particles from the spark would directly enter the main recirculation zone resulting from the velocity randomness and then ignite both sides of the combustor simultaneously. The second showed that flame particles from the spark would ignite the traversed regions following the swirl motion inside the combustor. The predicted ignition sequences were compared with the evolution of flame morphology recorded by high-speed imaging from experiments, showing qualitative agreement.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-10-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47356915","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

Turbulence anisotropy analysis at the middle section of a highly loaded 3D linear turbine cascade using Large Eddy Simulation 基于大涡模拟的高负荷三维线性涡轮叶栅中段湍流各向异性分析

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Journal of the Global Power and Propulsion Society Pub Date : 2022-09-14 DOI: 10.33737/jgpps/159784

Nima Fard afshar, D. Kožulović, Stefan Henninger, Johannes Deutsch, P. Bechlars

{"title":"Turbulence anisotropy analysis at the middle section of a highly loaded 3D linear turbine cascade using Large Eddy Simulation","authors":"Nima Fard afshar, D. Kožulović, Stefan Henninger, Johannes Deutsch, P. Bechlars","doi":"10.33737/jgpps/159784","DOIUrl":"https://doi.org/10.33737/jgpps/159784","url":null,"abstract":"This study analyzes the flow over a three-dimensional linear low-pressure turbine cascade blade using large eddy simulation at Re = 90,000. The computational model consists of one blade passage with periodic boundaries and synthetic turbulence is generated at the inlet of the domain. Various flow metrics, including isentropic Mach number distribution at mid-span and wake total pressure losses are compared with available experimental data and found to be in good agreement. A more detailed analysis of the turbulence with particular attention to the separation bubble region is subsequently presented. The analysis revealed that the turbulence is in a nearly two-component state very close to the wall region and gradually follows a certain anisotropy trajectory, as the distance from the wall increases. Even in the free-stream region no fully isotropic state is reached, due to large acceleration and flow turning. The results give a new insight into the state of turbulence within the separation region on the blade suction side and emphasize the deficiencies of the Reynolds-averaged Navier Stokes (RANS) turbulence models in reproducing the turbulence anisotropy. This insight is of relevance for the aerodynamic design of turbines, since large parts of the total pressure loss are generated in the separation region.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-09-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45427232","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

Investigation of turbulence production and dissipation due to isotropic and anisotropic roughness components on real surfaces 实际表面上各向同性和各向异性粗糙度分量引起的湍流产生和耗散研究

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Journal of the Global Power and Propulsion Society Pub Date : 2022-08-25 DOI: 10.33737/jgpps/151658

J. Ahrens, Sebastian Kurth, K. Cengiz, Lars Wein, J. Seume

{"title":"Investigation of turbulence production and dissipation due to isotropic and anisotropic roughness components on real surfaces","authors":"J. Ahrens, Sebastian Kurth, K. Cengiz, Lars Wein, J. Seume","doi":"10.33737/jgpps/151658","DOIUrl":"https://doi.org/10.33737/jgpps/151658","url":null,"abstract":"Roughness generally consists of structures that are either oriented anisotropic in directions tangential to the surface or isotropic, or a superposition of both components. Interactions between the roughness elements exert a significant influence on the fluid mechanical losses. Cost-effective maintenance of the functionality of the surfaces of aerodynamically relevant components such as blades requires the quantitative prediction of the influence on the flow, which can be achieved through Reynolds-Averaged-Navier-Stokes Simulations (RANS). An established roughness parameter used to model the influence on the flow is the equivalent sand grain roughness ks. By contrast, the research presented here employs Direct Numerical Simulations (DNS) with Immersed Boundary Method (IBM) of channel flows over anisotropic, isotropic, and superimposed surfaces in order to investigate the aerodynamic losses, for example, due to turbulent production and dissipation. The simulation results show that the equivalent sand grain roughness does not correctly predict flow losses from anisotropic and superimposed surfaces, because in reality, the “angle of attack” with respect to the anisotropic structures changes the turbulence due to altered turbulent production and dissipation. A non-linear relationship between the flow resistance and this angle of attack is a result of local changes in pressure gradients.","PeriodicalId":53002,"journal":{"name":"Journal of the Global Power and Propulsion Society","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44223152","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