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

{"title":"Detailed Design and Optimization of the First Stage of an Axial Supercritical CO2 Compressor","authors":"Matthew J. Ha, Justin Holder, S. Ghimire, Adam Ringheisen, M. Turner","doi":"10.1115/gt2022-82590","DOIUrl":"https://doi.org/10.1115/gt2022-82590","url":null,"abstract":"\u0000 Advancement in energy storage technology is critical in the transition to increased renewable energy sources. The thermodynamic properties of S-CO2 allow for high thermal efficiency and power density potential in turbomachinery design. Relative to the Steam Rankine and Air Brayton cycles, S-CO2 cycles benefit in performance, size, and cost.\u0000 As S-CO2 gains acceptance in the industry, research must be conducted to understand the potentials and limitations of this new technology; this is key to the eventual commercial viability of S-CO2 applications. Currently, applications of S-CO2 in turbomachinery are limited to centrifugal design due to the complex fluid properties and flow interactions.\u0000 Advancements in compressor design now allow for the intelligent navigation of this complex design space. Optimization tools are utilized to evaluate parametrically defined blades in S-CO2 working fluid to explore advanced, high-performance geometries.\u0000 The first axial S-CO2 compressor is designed using this optimization based methodology. This design is the scaled 9 MW 3 stage version of a larger 100 MW 9 stage compressor that will be used for an energy storage application. The adiabatic efficiency of the first stage design is estimated at 91.6% with 3.14 MW of power at 19,800 rpm. The blade height at the rotor leading edge is 3.28 cm.\u0000 The first stage of the scaled 9 MW 3 stage compressor will be tested at the University of Notre Dame Turbomachinery Lab; testing of the complete 3 stage machine will follow the single stage testing.\u0000 Stage one design drawings have been finalized and submitted for manufacturing. The IGV and Stator 1 have been manufactured and received by the University of Notre Dame Turbomachinery Lab for assembly and testing in the Fall of 2022.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"135 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":"131826549","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":"A Coupled Computational Aero-Acoustics (CAA)/ Large-Eddy Simulation (LES) Approach for the Pressure Calculation in Internal Low-Mach Number Flows","authors":"P. Bénez, G. Lartigue, V. Moureau, G. Ribert, Marine Robin","doi":"10.1115/gt2022-80476","DOIUrl":"https://doi.org/10.1115/gt2022-80476","url":null,"abstract":"\u0000 The predictive unsteady simulation of pressure fluctuations in turbulent internal flows at low-Mach number is challenging because of the very different propagation speeds of the acoustic and entropy waves. In this paper, a hybrid Computational-Aero-Acoustics (CAA) / Large-Eddy-Simulation (LES) approach tailored for the numerical calculation of aero-acoustic noise and pressure in internal low-Mach number flow is developed to alleviate the acoustic time step restriction. The algorithm is based on the coupling of a fractional-step method used to solve the low-Mach number Navier-Stokes equations and a fully-implicit linear acoustics solver. The pressure field resulting from the Helmholtz equation computed by the acoustic solver is composed of both dynamic and acoustic contributions. The Newmark’s time integration method combined with implicit Non-Reflecting-Boundary-Conditions (NRBC) are implemented for solving implicitly the Helmholtz equation and then advancing the two solvers with the same convective time step. The properties of the linear acoustic solver are illustrated on simple test cases and the coupling method is then validated by performing the aero-acoustic simulation of the isothermal flow in a complex semi-industrial burner.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"27 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":"114765933","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":"New Method for Cycle Performance Prediction Based on Detailed Compressor and Gas Turbine Flow Calculations","authors":"M. Petrovic, A. Wiedermann, M. Banjac, Srdjan Milic, Djordje Petkovic, Teodora Madzar","doi":"10.1115/gt2022-82229","DOIUrl":"https://doi.org/10.1115/gt2022-82229","url":null,"abstract":"\u0000 Gas turbines have made significant progress in recent years. The efficiencies of the compressor and turbine were improved based on achievements in aerodynamics, i.e., on the introduction of numerical flow simulation. The introduction of massive cooling and thermal barrier coating permitted a considerable increase in the turbine inlet temperature. These developments led to a significant increase in the thermal efficiency of gas turbines. However, most of the existing tools for predicting cycle performance are based on 0D compressor and turbine maps for the efficiency and pressure ratio as a function of the mass flow. Such tools cannot simulate all new trends in gas turbines in the most efficient way. The new method proposed here is a 2D method based on detailed flow calculations in the compressor and the gas turbine. Previously developed through-flow tools for compressor/turbine flow simulation and performance prediction were applied for this purpose. The processes in the compressor and the turbine are connected by calculation of the processes in the combustion chamber and the secondary and cooling air system. The turbine inlet temperature is determined by an iterative procedure. The method allows the accurate prediction of performance at every operating point. Air cooling bleeds in the compressor and its injections in the turbine blades can be simulated precisely. Also, adjustments of the inlet guide and stator vanes and their influence on compressor behavior can be accurately taken into account at every operating point. Finally, calculation of the combustion and the flow in the compressor and the turbine allows a simulation with correct gas composition and humidity of the air. The method is demonstrated on a case of an industrial gas turbine. The numerical results were compared with experimental data and showed very good agreement. The procedure is rapid and robust and permits optimization of the different solutions during the design phase.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"46 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":"122658140","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":"Transition Model Extension for Roughness Effects","authors":"D. Kožulović, Nemo Juchmann, A. Führing, C. Bode","doi":"10.1115/gt2022-83277","DOIUrl":"https://doi.org/10.1115/gt2022-83277","url":null,"abstract":"\u0000 Depending on the manufacturing process and the operating conditions, airfoil surface may show many different roughness characteristics, together with a significant influence at the boundary layer development. In this paper, only the influence at the laminar-turbulent transition is considered and modeled by an extension of the γ-ReΘ transition model of Langtry and Menter. Essentially, an additional transport equation for a roughness amplification scalar is used to modify the transition onset and development, as already presented by Dassler et al. in 2012. In the meantime, the calibrated functional relationship for Argr has been released for the publication for the first time in this paper. In addition, the model performance will be demonstrated and discussed on test cases with increasing complexity, including turbomachinery cascades and rigs.\u0000 As an input to the model, the equivalent sand-grain roughness is required. In this way, the versatile roughness characteristics of the investigated surface are reduced to only one parameter. The model has been implemented into the CFD software package TRACE of DLR Institute of Propulsion Technology. Only steady flow test cases have been investigated and validated. The transition intermittency is coupled to the two-equation turbulence model of Wilcox. In this model, the roughness influence at the fully turbulent boundary layers is also captured by the variation of the boundary condition for the specific turbulence dissipation rate ω.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"119 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":"132225547","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":"Analytical Modeling of the Injector Response to High Frequency Modes in a Tubular Multi-Jet-Combustor","authors":"J. Rosenkranz, T. Sattelmayer","doi":"10.1115/gt2022-81957","DOIUrl":"https://doi.org/10.1115/gt2022-81957","url":null,"abstract":"\u0000 Gas turbine combustors with multi-jet burners have been shown to provide better fuel flexibility compared to large swirl burners and can meet current low emissions standards at increasing turbine inlet temperatures. In case thermoacoustic combustion instabilities occur, the resonant feedback loop of the thermoacoustic mode in the chamber leads to injector coupling, which has not yet been investigated in same depth as in rocket engines in the past. The higher order mode inside the combustor initiates longitudinal modes in the upstream injector tubes leading to flame surface and location modulations as potential drivers of instability. Furthermore, fuel injection in the mixing tubes generate equivalence ratio fluctuations, which have an additional influence on flame dynamics. As these effects deteriorate emissions, flashback safety and lead to increased wear or even severe damage of the combustor, proper calculation of the acoustic injector response is an important aspect of combustor stability modelling. The paper at hand aims for an analytical model to describe the injector response to higher order modes as an alternative to the existing approaches, which are largely based on numerical computations. For this purpose, lumped parameter models are used to calculate the wave scattering at the injector tube-chamber interface. It is shown that the Rankine-Hugoniot conditions at the area jump can be applied to high frequency acoustics in a similar manner as to low frequency acoustics. Numerical simulations in COMSOL are used to verify the model for the first and second transversal and the first radial mode.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"17 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":"132825634","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":"GT2022 Front Matter","authors":"","doi":"10.1115/gt2022-fm10c","DOIUrl":"https://doi.org/10.1115/gt2022-fm10c","url":null,"abstract":"\u0000 The front matter for this proceedings is available by clicking on the PDF icon.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"R-13 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114128606","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":"Calibrated Rotation-Helicity-Quadratic Constitutive Relation Spalart-Allmaras (R-H-QCR SA) Model for the Prediction of Multi-Stage Compressor Characteristics","authors":"Kotaro Matsui, N. Tani, E. Perez, Ryan Kelly, A. Jemcov","doi":"10.1115/gt2022-82080","DOIUrl":"https://doi.org/10.1115/gt2022-82080","url":null,"abstract":"\u0000 Compressor performance prediction is still one of the significant interests in the turbomachinery research field. The two critical parameters for compressor design are adiabatic efficiency and stability margin. The Spalart-Allmaras (SA) turbulence model and modified SA models are widely used in that design process. However, the prediction accuracy is not always satisfactory. In most cases, the SA model predicts larger stall mass flow, and the RC-QCR SA model underestimates efficiency. This study proposes a new combination of the modified SA model (R-H-QCR model). R-H-QCR stands for Rotation-Helicity-Quadratic constitutive relation. The model increases or decreases turbulent viscosity based on flow rotation, energy backscatter, and anisotropy of turbulence flow field. The Bayesian inference framework calibrates the model parameters to predict accurately both efficiency and stability in the 3.5 stage compressor. The R-H-QCR, RC-QCR, and default SA models are evaluated in the multi-stage compressor. For the performance prediction, the R-H-QCR model predicts a better stability margin than the SA model and better efficiency than the RC-QCR model. In addition, the spanwise distribution of normalized total pressure is well captured by the R-H-QCR model, indicating that the R-H-QCR model improves flow field prediction.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"26 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":"134268355","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":"Predictions of Falling Wavy Films Based on the Depth Averaged Thin Film Model and Its Application to Aeroengine Bearing Chamber","authors":"K. Singh, A. Nicoli, R. Jefferson-Loveday, S. Ambrose, P. Paleo Cageao, K. Johnson, S. Mouvanal, J. Cao, A. Jacobs","doi":"10.1115/gt2022-78010","DOIUrl":"https://doi.org/10.1115/gt2022-78010","url":null,"abstract":"\u0000 In the present study, the evolution of a falling wavy film with upstream forced excitation is investigated using the depth averaged thin film model, known as Eulerian Thin Film Model (ETFM). Because of the depth averaging of the governing equations, coarse grids can be used in the wall normal direction. Consequently, this model is computationally efficient when compared to fully resolving thin films and hence highly advantageous for industrial simulations. In the case of a falling wavy film, film thickness and film velocity are closely coupled. A coupled solver that solves the depth averaged continuity and momentum equations simultaneously has been implemented with the provision to apply smoothing to the curvature of surface tension term to improve the accuracy and robustness of the model. The implemented model provides a stable solution for explicit as well as implicit temporal formulations. The performance of the newly implemented ETFM model is evaluated by comparing numerical results with experimental measurements and high-fidelity VOF simulations. The newly implemented model is found to be reliable in predicting free surface film profiles. It is 150 to 415 times computationally cheaper when compared to high-fidelity VOF simulations. The implemented and validated model is successfully used to predict a wavy film on the inlet of a representative aeroengine bearing chamber. The model is able to capture key flow physics on the front face of a static insert, which forms part of the bearing chamber inlet, and agrees well with experimental visualization of oil flow on the insert.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"21 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":"133478047","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":"High Accuracy Numerical Investigation of Trailing Edge Noise at Vortex Shedding Critical Angle of Attack","authors":"Huabin Zheng, Jinqiang Chen, P. Yu, H. Ouyang","doi":"10.1115/gt2022-83143","DOIUrl":"https://doi.org/10.1115/gt2022-83143","url":null,"abstract":"\u0000 In this paper, the trailing edge noise generated by a 2D airfoil around the critical angle of attack for vortex shedding is numerically investigated using an in-house code with high accuracy and efficiency. In the present method, a fourth-order upwind compact finite-difference scheme with dispersion relation preserving (DRP) property is applied for the convection terms, and a fourth-order Runge-Kutta scheme is used for temporal discretization. The reflection of sound on the boundary is suppressed with Navier-Stokes characteristics boundary condition (NSCBC). To improve computational efficiency, a novel parallel computing strategy for the high-order compact schemes is employed. Thus, direct numerical simulation (DNS) can be realized for the flows of low Reynolds number (Re), while implicit large eddy simulation (ILES) would be carried for the flows of high Reynolds number. The present numerical method is validated by comparing the lift coefficient, drag coefficient and Strouhal number (St) to the previous publications. Based on the high accuracy and high-fidelity method, the flow field and sound field of a two-dimensional NACA0012 airfoil around critical angle of attack (AoA) at Re = 1000 are simultaneously solved. The results indicate that sound source is dipole centered at the surface of the airfoil at vortex shedding frequency, and is dipole, quadrupole or more complex sources located at the wake close to the trailing edge at higher order frequencies. These findings will help to improve understanding about the generation and propagation mechanisms of trailing edge noises at low Reynolds number.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"7 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":"133224503","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":"Development of Machine-Learnt Turbulence Closures for Wake Mixing Predictions in Low-Pressure Turbines","authors":"Yuri Frey Marioni, P. Adami, Raul Vázquez Díaz, Andrea Cassinelli, S. Sherwin, F. Montomoli","doi":"10.1115/gt2022-82531","DOIUrl":"https://doi.org/10.1115/gt2022-82531","url":null,"abstract":"\u0000 In this work, a DNS – Machine Learning (ML) framework is developed for low-pressure turbine (LPT) profiles to inform turbulence closures in Reynolds-Averaged Navier-Stokes (RANS) calculations. This is done by training the coeffcients of Explicit Algebraic Reynolds Stress Models (EARSM) with shallow artificial neural networks (ANN) as a function of input flow features. DNS data are generated with the incompressible Navier-Stokes solver in Nektar++ and validated against experiments. All calculations include moving bars upstream of the profile to capture the effect of incoming wakes. The resulting formulations are then implemented in the Rolls-Royce solver HYDRA and tested a posteriori. The aim is to improve mixing predictions in LPT wakes, compared to the baseline model, Wilcox’s k-ω SST, in terms of velocity profiles, turbulent kinetic energy (TKE) production and mixing losses. LPT calculations are run at Reynolds numbers spanning from ≈ 80k to ≈ 300k, to cover the range of aircraft engine applications. Models for the low and high Reynolds datasets are trained separately and a method is developed to merge the two together. The resulting model is tested on an intermediate Reynolds case. This process is followed for two computational domains: one starting downstream of the profile trailing edge and one including the last portion of the profile. Finally, the developed closures are tested on the entire profile, to confirm the validity of the improvements when the additional effect of transition is included in the simulation. This work explains the methodology used to develop ML-driven closures and shows how it is possible to combine models trained on different datasets.","PeriodicalId":191970,"journal":{"name":"Volume 10C: Turbomachinery — Design Methods and CFD Modeling for Turbomachinery; Ducts, Noise, and Component Interactions","volume":"31 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":"126195997","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}