Development and Validation of a Massively Parallel Flow Solver for Turbomachinery Flows (original) (raw)
Related papers
A Parallel Algorithm for Simulation of Unsteady Flows in Multistage Turbomachinery
International Journal of Turbo and Jet Engines, 2001
The numerical simulation of unsteady flow in multi-stage turbomachinery is computationally expensive. A parallel code using message-passing interface libraries, which was developed to reduce the turnaround time and the cost of computation, is presented in this paper. The paper describes the details of the parallel algorithm, including the parallelization rationale, domain decomposition and processor allocation, and communication patterns. The numerical algorithm was used to simulate the unsteady flow in a six-row test turbine. The numerical results present the salient features of the turbine flow, such as the temporal and spatial vari-*-Total (or stagnation)
A New Procedure for Simulating Unsteady Flows Through Turbomachinery Blade Passages
Volume 1: Turbomachinery, 1994
This paper outlines the development of two new unsteady wake-blade row aerodynamic interaction models and a rotorstator unsteady aerodynamic interaction model. These flow models take, as input, solutions from Adamczyk's averagepassage flow model to provide an initial guess as to the transport of vortical, entropic and potential disturbances through a blade row. The response to these disturbances is calculated using an unsteady code known as MSUTC. This code solves the full Reynolds-averaged form of the Navier-Stokes equations using a modified Baldwin-Lomax turbulence model. The code can run with and without the use of wall functions. The solver is an implicit finite volume scheme with flux Jacobians evaluated by flux-vector splitting and residual fluxes by Roe's flux-difference splitting. A series of simulations will show that the CPU time for all three models is nearly two orders of magnitude faster than current rotor-stator numerical simulation models. In addition, because of the numerical efficiency of the models, routine execution of numerical experiments for gaining insight into the flow processes controlling turbomachinery blade row performance become practical.
Unsteady flow investigations in an axial turbine using the massively parallel flow solver TFLO
39th Aerospace Sciences Meeting and Exhibit, 2001
The results from two numerical simulations of the unsteady flow in a 1-1/2 stage axialflow turbine are presented and compared with experimental data to show both the effect of blade count on the solution accuracy and the time-averaged and unsteady flow physics present. The TFLO three-dimensional, multi-block, massively parallel turbomachinery flow solution procedure is used to simulate the flow through the Aachen 36-vane/41blade/36-vane 1-1/2 stage turbine rig. Comparisons of the time-averaged and unsteady flow solutions of 1-vane/1-blade/1-vane and 6-vane/7-blade/6-vane configurations with the available experimental data are used to show the importance of matching actual blade counts in unsteady flow simulations as closely as possible. In addition, these comparisons are used to quantify the predicted aerodynamic performance differences and highlight the different unsteady flow physics in the two simulations.
International Conference on High Performance Computing in the Asia-Pacific Region, 2000
The three-dimensional multi-stage turbomachinery flow simulation is calculated on the PC cluster environment in NCHC. The UTRC large-scale turbine is employed here as the baseline configuration. A compressible viscous finite volume algorithm solving Reynolds averaged Navier-Stokes equations with artificial dissipation terms similar to Jameson's method is adopted circumferential average is performed between the interface of rotor and stator. The master/slave
The Development of New CFD Solver for 3D Turbomachinery Flow Computations
The concept of the new CFD solver for the 3D turbomachinery flow simulation using the RANS equations is considered. The governing equations are supplemented with the k-ω SST turbulence model. The realisability constraints and the special boundary conditions for adverse pressure gradient flows are shown to be important. An improved numerical technique is suggested to increase efficiency and robustness of the computational procedure. Numerical results for selected test cases are presented. Screenshots of the developed software are shown.
A Navier Stokes Solver for Axisymmetric Turbomachinery Analysis
2010
Abstract. An axysimmetric Navier Stokes solver is presented and applied to the analysis of multi-stage turbomachinery. As in classical through flow computations, some 3D effects are taken into account by means of appropriate source terms. In particular, the effect of the blade is modeled introducing a blade blockage and blade force, which has both a component normal to the flow path and one along the flow path, the latter introducing the viscous losses. The use of full Navier Stokes equations, however, allows to implicitly take into account some effects related to end wall boundary layers, as well as entropy radial redistribution and tip leakage flows, and nicely fits into a coherent workflow which couple axysimmetric quick preliminar design step to a complete 3d analysis for the best solutions. Despite the use of a rather crude loss and deviation model, the code demonstrates satisfying accuracy through comparison with experimental and computational data for a subsonic, four stage t...
Development of a Segregated Compressible Flow Solver for Turbomachinery Simulations
A steady multiple reference frame segregated compressible solver and an unsteady sliding mesh one are developed using OpenFOAM® to simulate turbomachinery. For each of the two solvers, governing equations, numerical approach and solver structure are explained. Pressure and energy equation are implemented so as to obtain the best numerical properties, such as the ability to use large time-steps. Sod shock tube test case is used to assess the prediction of compressible phenomena by the transient scheme, which shows proper resolution of compressible waves. Both solvers are used to simulate a turbocharger turbine, comparing their solutions to corresponding ones using ANSYS ® Fluent ® as a means of validation. The multiple reference frame solver global results quantitatively differ from those computed using ANSYS Fluent, although predicted flow features match. The solution obtained by the sliding mesh solver presents better agreement compared to ANSYS Fluent one.
Computational Fluid Dynamics in Turbomachinery: A Review of State of the Art
Computational fluid dynamics (CFD) plays an essential role to analyze fluid flows and heat transfer situations by using numerical methods. Turbomachines involve internal and external fluid flow problems in compressors and turbines. CFD at present is one of the most important tools to design and analyze all types of turbomachinery. The main purpose of this paper is to review the state of the art work carried out in the field of turbomachinery using CFD. Literature review of research work pertaining to CFD analysis in turbines, compressors and centrifugal pumps are described. Various issues of CFD codes used in turbomachinery and its parallelization strategy adopted are highlighted. Furthermore, the prevailing merits and demerits of CFD in turbomachinery are provided. Open areas pertinent to CFD investigation in turbomachinery and CFD code parallelization are also described.