Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions最新文献

{"title":"Flow Design Using CFD for a Constant-Section Recursive Sequential Combustor","authors":"Andrea Hofer, Nina Paulitsch, F. Giuliani","doi":"10.1115/gt2022-82420","DOIUrl":"https://doi.org/10.1115/gt2022-82420","url":null,"abstract":"\u0000 The project MOeBIUS stands for MOmentum-Enhanced Blend of the reactants with recIrculated bUrnt gaseS. It is a new combustion concept based on the principle of recursive sequential combustion (RSC), as described in paper GT2021-59592. The aim is to assert the feasibility of a recursive sequential combustor using CFD simulations and to evaluate the most promising flow design for a 3D printed prototype. This paper focuses on the latest developments of the variant called constant section, with a short overview of the geometry’s design iterations. Based on previous simulation results the combustion chamber is torus-shaped with a double-spiral-like cross section. The simulated domain covers a sector of the torus, with interpolated results to augment the data points. Two air inlets and one fuel inlet (currently modelled with Methane) feed the combustion chamber to create a stable, lean, and continuous flame. Flue gas is partly fed back into the combustion process, this recirculation increases lean combustion robustness and decreases the amount of generated nitrogen oxides. The circular combustion chamber and guiding vanes in the in- an outlet pipes generate a flow dynamic that combines a swirling motion necessary to stabilise the flame to a flow circulation along the torus. This flow pattern is driven by the elevated momentum flux at the injection. The air outlet is designed to enforce interaction between outgoing burnt gasses and fresh inlets while facilitating the split of a fraction of the flue gas that follows the torus’ curvature. The simulations confirm the presence of a large swirl in the chambers section, as well as the maintenance of a circulation in the toroidal direction, which is essential to the concept. This is in good agreement with the desired flow design, and the constant section concept is therefore feasible and valid. Ongoing simulations implying fine-tuning of the parameters are carried out in 3D to ensure stable combustion behaviour and meet expectations in terms of functionality.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115177772","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}

{"title":"Mesh Refinement and Inlet Turbulence Intensity in the Numerical Evaluation of Cooling Effectiveness: A Systematic Study on an Industrial Gas Turbine","authors":"F. Lo Presti, Benjamin Winhart, Pascal Post, Francesca di Mare, A. Wiedermann, Johannes Greving, Robert Krewinkel","doi":"10.1115/gt2022-80958","DOIUrl":"https://doi.org/10.1115/gt2022-80958","url":null,"abstract":"\u0000 In this study, the influence of grid resolution and inflow turbulence on the prediction of gas temperature distribution around HP-turbine blades and the effectiveness of cooling flows are assessed by means of a comparative, systematic study with increasing grid resolution, starting from a typical RANS-mesh with progressive refinement, by means of scale-resolving simulations. The investigation is focused on a three-stage industrial gas turbine in the mid-range output class, whereby we restrict our analysis to the first stage, where most of the external cooling flow is injected, this regions being characterized by the highest temperature fluctuations. The extent of these variations and their unsteady characteristics need to be determined to verify if they have a measurable influence on the material temperature. As the interaction of turbulence with cooling flows is a key element in the prediction of cooling effectiveness, turbulence levels play a major role in addition to the grid resolution. Therefore, special attention is paid to the accurate description of turbulence scaling laws and correlations at the turbine inflow. The results of the investigation provide insight in a viable modelling and simulation tool which can be adopted during design cycles and reveals valuable details of the unsteady aerothermal stresses on the HP turbine blades.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129816088","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}

{"title":"Numerical Investigation of a Turbine Vane Frame for Co- and Counter-Rotating Configuration","authors":"Nicolas Krajnc, F. Merli, Asim Hafizovic, A. Peters, E. Göttlich","doi":"10.1115/gt2022-81083","DOIUrl":"https://doi.org/10.1115/gt2022-81083","url":null,"abstract":"\u0000 This paper presents the numerical comparison of a turbine vane frame (TVF) for future high-bypass turbofan engines for architectures with a co-rotating setup between the high-pressure turbine (HPT) and the low-pressure turbine (LPT) and with a counter-rotating setup. The flow field in the TVF is impacted by the decision of a co- or counter-rotating architecture which is driven not only by aerodynamics but also by the dynamic and mechanical design constraints in an engine.\u0000 As boundary conditions for the steady RANS simulation, measurements are used which were carried out in the engine-representative two-spool rig at the Institute for Thermal Turbomachinery and Machine Dynamics at the Graz University of Technology. The test vehicle in this rig consists of an HPT with nearly axial exit flow and a counter-rotating LPT connected via the TVF with aft-loaded struts and splitters. To reproduce a realistic HPT flow field, purge air is provided by a secondary air system (SAS). The inlet and outlet boundary conditions are defined based on the five-hole probe (5HP) measurement set up- and downstream of the TVF, acquired for three different purge conditions (0%, 100% = nominal, and 200%).\u0000 To simulate a co-rotating configuration, the measured inlet flow field has been mirrored. The focus of this paper is to gain additional insights into the general flow behavior of a TVF in a co- and counter-rotating configuration, respectively. A special focus is placed on the differences between the development of strut secondary flows on their way through the TVF depending on the inlet flow field. Additionally, a duct loss comparison of the two configurations and its sensitivity to different purge flow levels is presented.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122733527","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}

{"title":"Modeling of Inviscid Flow Shock Formation in a Wedge-Shaped Domain Using a Physics-Informed Neural Network-Based Partial Differential Equation Solver","authors":"R. Laubscher, P. Rousseau, C. Meyer","doi":"10.1115/gt2022-81768","DOIUrl":"https://doi.org/10.1115/gt2022-81768","url":null,"abstract":"\u0000 Physics-informed neural networks (PINN) can potentially be applied to develop computationally efficient surrogate models, perform anomaly detection, and develop time-series forecasting models. However, predicting small-scale features such as the exact location of shocks and the associated rapid changes in fluid properties across it, have proven to be challenging when using standard PINN architectures, due to spatial biasing during network training. This paper investigates the ability of PINNs to capture these features of an oblique shock by applying Fourier feature network architectures. Four PINN architectures are applied namely a standard PINN architecture with the direct and indirect implementation of the ideal gas equation of state, as well as the direct implementation combined with a standard and modified Fourier feature transformation function. The case study is 2D steady-state compressible Euler flow over a 15° wedge at a Mach number of 5. The PINN predictions are compared to results generated using proven numerical CFD techniques. The results show that the indirect implementation of the equation of state is unable to enforce the prescribed boundary conditions. The application of the Fourier feature up-sampling to the low-dimensional spatial coordinates improves the ability of the PINN model to capture the small-scale features, with the standard implementation performing better than the modified version.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126344357","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}

{"title":"Design Optimization of Integrated Anti-Rotation Feature for Power Turbine Nozzles","authors":"Abhimanyu Soman, S. Colantoni","doi":"10.1115/gt2022-78254","DOIUrl":"https://doi.org/10.1115/gt2022-78254","url":null,"abstract":"\u0000 Gas turbine nozzles are static components that are meant to turn and accelerate high temperature, high pressure, and low-velocity flue gas into the downstream turbine row of buckets. During gas turbine operation, nozzles are subjected to high-pressure load due to the expansion of flue gases, in axial and tangential directions. This creates a tendency for nozzle movement in tangential direction which has potential to create flow disturbance and intersegment gap opening. To prevent this movement, it should be held in tangential direction firmly by introducing an anti-rotation feature. A slot is introduced in the nozzle outer sidewall and a pin connected with casing in such a way that the nozzle’s tangential movement is restrained. As the nozzle’ s outer sidewall experiences high thermal gradients in the operating condition, it induces high stress at the nozzle anti-rotation feature. There are many possible design options available to mitigate this challenge. In the present work, anti-rotation feature is integrated with the nozzle’s outer sidewall and a matching slot is provided in the casing. A detailed study is performed to optimize this anti-rotation feature to reduce high thermal-mechanical stress and thereby improve reliability. The low cycle fatigue life is one of the vital requirements in improving reliability. The low cycle fatigue life of the optimized anti-rotation feature is validated using the finite element analysis. This paper describes the process step details in optimizing the anti-rotation feature.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"36 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126129746","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}

{"title":"Parametric Studies and Simulations of a Hydrogen Micromix Combustor","authors":"A. French, G. Mingione, A. Schettino, P. Roncioni, P. Vitagliano, M. Minervino","doi":"10.1115/gt2022-81784","DOIUrl":"https://doi.org/10.1115/gt2022-81784","url":null,"abstract":"\u0000 The use of hydrogen as an alternative fuel in the combustion chamber of an aircraft turbine engine would offer a practical solution to reducing levels of emissions which contribute to atmospheric pollution. In recent years various designs of the basic system component of such an engine have been proposed being described as the hydrogen micromix combustor. This technology requires the design and development of a safe mechanism for hydrogen combustion which avoids auto-ignition and flashback and permits the initial balance and mixing of a hydrogen-air mixture to produce thrust from the combustion of hundreds of miniature low temperature diffusion flames which produce extremely low levels of NOx.\u0000 In this paper a potential geometry and typical operating conditions of such a micromix combustor has been selected for a critical examination of the numerical modelling with particular attention to the levels of NOx predicted. In particular the level of grid independence of the NOx modelling is assessed as well as the variations in NOx levels generated in the march towards steady state solutions for various numerical methods.\u0000 Additionally, a series of parametric studies associated with modifications of the basic micromix combustor design are explored to verify both the consistency in the numerical methods adopted as well as assessing the impact of such modifications on the overall micromix combustor performance.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126175893","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}

{"title":"Large Eddy Simulation of Turbulent Flow Through a Compressor Cascade","authors":"Syed Anjum Haider Rizvi, J. Mathew","doi":"10.1115/gt2022-83081","DOIUrl":"https://doi.org/10.1115/gt2022-83081","url":null,"abstract":"\u0000 A study of large eddy simulations (LES) for compressor blade flows has been undertaken and assessed by comparisons with the measurements of Hobson et al. (AIAA J. Prop. Power, 17, 154 (2001)) on a linear cascade of controlled-diffusion airfoils at Reynolds numbers based on blade chord and inflow velocity of 210 000, 380 000 and 640 000. LES of the latter two conditions are reported here. LES is by an explicit filtering method. Compressible flow equations in curvilinear coordinates were solved with 8th-order, central, finite differences and 2nd order Runge-Kutta integration. At 380 000 there is close quantitative agreement of the blade surface pressures and blade normal profiles of velocity magnitudes and fluctuations. Features of the initial development of the suction surface boundary layer is typical of transition induced by freestream turbulence, but end-stage turbulent spots are missing because of premature completion of transition over a mid-chord separation bubble. At 640 000 this separation is absent and turbulent spots appear before transition is completed. Blade surface pressure distribution from the LES agrees closely with that from experiment and is consistent with absence of separation, as are velocity profiles. Velocity profiles from experiment however had shown substantial open separation from the suction surface. This discrepancy had been noted before and was supposed to be an endwall effect, but our LES, including one with endwalls, does not support that view.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"60 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124560392","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}

{"title":"Validation of an Analytical Model for the Acoustic Impedance Eduction of Multi-Cavity Resonant Liners by a High-Fidelity LES Approach","authors":"S. Giaccherini, L. Pinelli, M. Marconcini, R. Pacciani, A. Arnone","doi":"10.1115/gt2022-81984","DOIUrl":"https://doi.org/10.1115/gt2022-81984","url":null,"abstract":"\u0000 The massive growth of the air traffic during the last years is leading to stricter limitations on the noise emission levels radiated from aircraft engines. To face this issue, the installation of acoustic liners on the intake duct and the exhaust nozzles is a common strategy adopted to properly abate noise emissions coming from the fan, the compressor, the turbine, and the jet.\u0000 In this context, the aim of the present paper is to use high-fidelity LES simulations to validate a MDOF (multi-degree of freedom) extension of the single- and double-degree of freedom (SDOF and DDOF) analytical model provided by Hersh for impedance eduction of acoustic liners.\u0000 Firstly, the results of the original Hersh model are compared with LES calculations performed with the OpenFOAM suite on a single-orifice and single-cavity layout (SDOF). Then the extension of the Hersh model to multi-cavity (MDOF) geometries by using a recursive formulation is presented. Finally, high fidelity simulations are carried out for single-orifice and multi-cavity (MDOF) configurations to validate the method extension and to understand how resonant coupling and acoustic impedance are affected by multi-cavity resonant elements.\u0000 The excellent agreement between the high-fidelity results and the analytical predictions for the single-cavity pattern confirms that the Hersh model is a useful formulation for a preliminary design of a SDOF acoustic liner. The model extension to MDOF configurations enables the designers to broaden the design space, and thus a validated analytical method is strictly necessary to perform sensitivity studies to the multi-cavity geometrical parameters (i.e., face-sheet thickness, cavities depth, porosity). Basically, a multi-cavity configuration makes the liner element resonate at different frequencies leading to multiple absorption peaks in the audible range. In this way, the acoustic performance of the liner is extended to a wider frequency range, overcoming the limitations of a traditional SDOF configuration.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125495323","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}

{"title":"The Impact of Inlet Flow Angle on Turbine Vane Frame Aerodynamic Performance","authors":"S. Pramstrahler, A. Peters, M. L. García De Albéniz, P. Leitl, F. Heitmeir, A. Marn","doi":"10.1115/gt2022-78065","DOIUrl":"https://doi.org/10.1115/gt2022-78065","url":null,"abstract":"\u0000 Modern aero-engines are designed for high efficiency and low weight to reduce fuel consumption and achieve reductions in CO2 emissions. According to the goals and roadmap of the “Flightpath 2050” report, the Strategic Research and Innovation Agenda (SRIA) demands a drastic reduction of emissions to balance further air traffic growth. Therefore, technologies and processes allowing for a 75 % reduction in CO2 emissions per passenger kilometer compared to the year 2000 technology standard must be available by 2050. Turbine Vane Frames (TVF) are one technology to increase the efficiency of aero-engines and can therefore help to reach this goal. Turbine Vane Frames are located in-between the high-pressure turbine (HPT) and the low-pressure turbine (LPT) of an aero-engine and have three major purposes: guiding the flow to higher radii, incorporating the function of stator guide vanes of the first stage of the LPT, and passing structural components and oil pipes through the flow channel. A TVF with aft-loaded wide-chord main vanes and splitter vanes was designed, which meets engine-representative mechanical and aerodynamic constraints. A test vehicle consisting of the TVF and a first-stage LPT rotor has been designed and is currently being tested in the subsonic test turbine facility for aerodynamic, aeroacoustic and aeroelastic investigations (STTF-AAAI) at the Graz University of Technology. In the engine, the TVF needs to function at high performance not only at the aerodynamic design point (cruise) but also at off-design conditions. A splittered TVF design features complex flow fields with strong secondary flow interactions, and because of the fundamental design differences, the flow field characteristics within a TVF are different from those in a conventional LPT vane row. This paper discusses the flow field in a splittered TVF with emphasis on secondary flow structures and their interaction with each other and the main flow. To examine the influence of different swirl angle levels on the flow field and loss generation mechanisms inside the TVF, the swirl angle upstream of the TVF is numerically changed in a wide range from positive to negative angles. The objective of this study is to examine the sensitivity of the splitter vanes to large flow angle deviations, as present in part-load operation. Additionally, the flow field downstream of the TVF and its influence on the LPT rotor performance is described in detail. The size and locations of separated flow regions resulting from the off-design incidence of the flow and their impact on the rotor are investigated and quantified. A loss breakdown is presented to discuss the impact of incidence variations on the performance of both the TVF and the LPT.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"105 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133337068","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}

{"title":"Gas Turbine Transition Duct Design Considerations","authors":"Aparna Satheesh, S. Manoharan, Sendilkumaran Soundiramourty, S. Babu","doi":"10.1115/gt2022-81670","DOIUrl":"https://doi.org/10.1115/gt2022-81670","url":null,"abstract":"\u0000 The gas turbine twin shaft variant requires an aerodynamic coupling between its high-pressure gas generator module and low-pressure power module. These two modules are spaced apart for aerodynamic and mechanical reasons. Typically, this is achieved by having a transition duct (TD) in between these two modules which smoothly allows the gas flow from HP turbine to LP turbine. To fulfill this purpose, it includes a radial inner shell and a radial outer shell defining a flow passage and radial struts which connects inner shell and outer shell. Cross-section of these struts are airfoil shaped to facilitate smooth flow of flue gas through TD. In addition, TD allows flow passage for cooling medium, support seals to prevent leakage at various interface locations and holds thermo-well for temperature measurement. Considering thermal and mechanical loads on the TD for standard operating conditions, Low cycle fatigue, creep and oxidation calculations are performed to ensure durability of TD design and necessary design changes are made to fulfill product requirement. Suitable material is selected, and manufacturing method finalized based on the design analysis. While standard offerings of gas turbine fulfill majority of requirements, there are some off-design or customized requirements which require detailed study. To fulfill these types of customized requirements, standard offerings of gas turbine are further analyzed for changed thermal boundary condition. These types of customizations facilitate running gas turbine with different options with a clear understanding of how it impacts durability. Through these studies, necessary maintenance factors are established to arrive at revised maintenance intervals based on severity of change. Low cycle fatigue, creep and oxidation calculations are performed with changed boundary condition also and maintenance factor is determined. This paper is intended to describe the steps followed in determining durability, establish maintenance factor and provide service recommendations.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"74 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131643069","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}