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Relevant bibliographies by topics / Turbomachinery; CFD

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Academic literature on the topic 'Turbomachinery; CFD'

Author: Grafiati

Published: 4 June 2021

Last updated: 15 February 2022

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Journal articles on the topic "Turbomachinery; CFD"

1

Blech, R. A., E. J. Milner, A. Quealy, and S. E. Townsend. "Turbomachinery CFD on parallel computers." Computing Systems in Engineering 3, no. 6 (December 1992): 613–23. http://dx.doi.org/10.1016/0956-0521(92)90013-9.

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2

Denton, J. D., and W. N. Dawes. "Computational fluid dynamics for turbomachinery design." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 213, no. 2 (February 1, 1998): 107–24. http://dx.doi.org/10.1243/0954406991522211.

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Computational fluid dynamics (CFD) probably plays a greater part in the aerodynamic design of turbomachinery than it does in any other engineering application. For many years the design of a modern turbine or compressor has been unthinkable without the help of CFD and this dependence has increased as more of the flow becomes amenable to numerical prediction. The benefits of CFD range from shorter design cycles to better performance and reduced costs and weight. This paper presents a review of the main CFD methods in use, discusses their advantages and limitations and points out where further developments are required. The paper is concerned with the application of CFD and does not describe the numerical methods or turbulence modelling in any detail.

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3

Chew, John W., and Nicholas J. Hills. "Computational fluid dynamics for turbomachinery internal air systems." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 365, no. 1859 (May 22, 2007): 2587–611. http://dx.doi.org/10.1098/rsta.2007.2022.

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Considerable progress in development and application of computational fluid dynamics (CFD) for aeroengine internal flow systems has been made in recent years. CFD is regularly used in industry for assessment of air systems, and the performance of CFD for basic axisymmetric rotor/rotor and stator/rotor disc cavities with radial throughflow is largely understood and documented. Incorporation of three-dimensional geometrical features and calculation of unsteady flows are becoming commonplace. Automation of CFD, coupling with thermal models of the solid components, and extension of CFD models to include both air system and main gas path flows are current areas of development. CFD is also being used as a research tool to investigate a number of flow phenomena that are not yet fully understood. These include buoyancy-affected flows in rotating cavities, rim seal flows and mixed air/oil flows. Large eddy simulation has shown considerable promise for the buoyancy-driven flows and its use for air system flows is expected to expand in the future.

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Hills, N. "Achieving high parallel performance for an unstructured unsteady turbomachinery CFD code." Aeronautical Journal 111, no. 1117 (March 2007): 185–93. http://dx.doi.org/10.1017/s0001924000004449.

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This paper describes the work done to achieve high parallel performance for an unstructured, unsteady turbomachinery computational fluid dynamics (CFD) code. The aim of the work described here is to be able to scale problems to the thousands of processors that current and future machine architectures will provide. The CFD code is in design use in industry and is also used as a research tool at a number of universities. High parallel scalability has been achieved for a range of turbomachinery test cases, from steady-state hexahedral mesh cases to fully unsteady unstructured mesh cases. This has been achieved by a combination of code modification and consideration of the parallel partitioning strategy and resulting load balancing. A sliding plane option is necessary to run fully unsteady multistage turbomachinery test cases and this has been implemented within the CFD code. Sample CFD calculations of a full turbine including parts of the internal air system are presented.

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Adamczyk, John J. "Aerodynamic Analysis of Multistage Turbomachinery Flows in Support of Aerodynamic Design." Journal of Turbomachinery 122, no. 2 (February 1, 1999): 189–217. http://dx.doi.org/10.1115/1.555439.

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This paper summarizes the state of 3D CFD based models of the time-averaged flow field within axial flow multistage turbomachines. Emphasis is placed on models that are compatible with the industrial design environment and those models that offer the potential of providing credible results at both design and off-design operating conditions. The need to develop models free of aerodynamic input from semiempirical design systems is stressed. The accuracy of such models is shown to be dependent upon their ability to account for the unsteady flow environment in multistage turbomachinery. The relevant flow physics associated with some of the unsteady flow processes present in axial flow multistage machinery are presented along with procedures that can be used to account for them in 3D CFD simulations. Sample results are presented for both axial flow compressors and axial flow turbines that help to illustrate the enhanced predictive capabilities afforded by including these procedures in 3D CFD simulations. Finally, suggestions are given for future work on the development of time-averaged flow models. [S0889-504X(00)02002-X]

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Ishida, H., N. Yamasaki, and M. Aotsuka. "Linear Unsteady CFD of Vibrating Blades of Turbomachinery." Procedia Engineering 67 (2013): 197–206. http://dx.doi.org/10.1016/j.proeng.2013.12.019.

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Koptilin, R. M., and A. V. Gaynutdinov. "Market overview CAE solutions for hydro, fluid dynamics of turbomachines." Informacionno-technologicheskij vestnik 13, no. 3 (September 30, 2017): 94–105. http://dx.doi.org/10.21499/2409-1650-2017-3-94-105.

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In this article the review of the market of software complexes for solving the problems of hydro- and gas dynamics of turbomachines is given. In the course of the work, CAE systems were analyzed to solve problems in this area. In the course of the analysis, the main possibilities, physical models, methods of solving problems used in this software were considered. Comparison of the functional of CFD analysis systems was carried out, the same and distinctive properties of the modeling systems of processes occurring in turbomachinery were identified.

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Dawes, W. N. "Turbomachinery computational fluid dynamics: asymptotes and paradigm shifts." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 365, no. 1859 (May 22, 2007): 2553–85. http://dx.doi.org/10.1098/rsta.2007.2021.

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This paper reviews the development of computational fluid dynamics (CFD) specifically for turbomachinery simulations and with a particular focus on application to problems with complex geometry. The review is structured by considering this development as a series of paradigm shifts, followed by asymptotes. The original S1–S2 blade–blade-throughflow model is briefly described, followed by the development of two-dimensional then three-dimensional blade–blade analysis. This in turn evolved from inviscid to viscous analysis and then from steady to unsteady flow simulations. This development trajectory led over a surprisingly small number of years to an accepted approach—a ‘CFD orthodoxy’. A very important current area of intense interest and activity in turbomachinery simulation is in accounting for real geometry effects, not just in the secondary air and turbine cooling systems but also associated with the primary path. The requirements here are threefold: capturing and representing these geometries in a computer model; making rapid design changes to these complex geometries; and managing the very large associated computational models on PC clusters. Accordingly, the challenges in the application of the current CFD orthodoxy to complex geometries are described in some detail. The main aim of this paper is to argue that the current CFD orthodoxy is on a new asymptote and is not in fact suited for application to complex geometries and that a paradigm shift must be sought. In particular, the new paradigm must be geometry centric and inherently parallel without serial bottlenecks. The main contribution of this paper is to describe such a potential paradigm shift, inspired by the animation industry, based on a fundamental shift in perspective from explicit to implicit geometry and then illustrate this with a number of applications to turbomachinery.

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Chew, J. W. "Developments in turbomachinery internal air systems." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, no. 1 (December 1, 2008): 189–234. http://dx.doi.org/10.1243/09544062jmes1140.

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Development of turbomachinery technology, including aircraft propulsion, has been an outstanding achievement of the last 50 years and, as illustrated by Ruffles in his paper ‘The future of aircraft propulsion’ (2000), further advances are expected in the future. Here, one particular aspect of turbomachinery technology, the internal air system is considered. An article by Dixon et al., published by the Institution of Mechanical Engineers in 2004, shows how computational modelling has become central to the design process and the importance of the internal air system in engine design. Bayley and Conway's 1964 paper, motivated by shortcomings in industrial design methods and understanding, was one of the first investigations of flow and heat transfer in rotating disc cavities typical of internal air systems. During the study, a theoretical or numerical treatment was considered intractable and so experiments were undertaken. These paved the way for an extensive research in this area. Today, the use of computational fluid dynamics (CFD) in industry for internal air flow prediction is commonplace. In this review, it is shown that the unshrouded disc cavity flow considered by Bayley and Conway is still challenging for modern CFD methods, and so the experimental data remain of interest to researchers in the field.

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Pujol, T., L. Montoro, M. Pelegrí, and J. R. González. "Learning hydraulic turbomachinery with computational fluid dynamics (CFD) codes." Computer Applications in Engineering Education 21, no. 4 (December 29, 2010): 684–90. http://dx.doi.org/10.1002/cae.20513.

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Dissertations / Theses on the topic "Turbomachinery; CFD"

1

Singh, Rajkeshar. "Application of generalized grids to turbomachinery CFD simulations." Thesis, Mississippi State : Mississippi State University, 2002. http://library.msstate.edu/etd/show.asp?etd=etd-07242002-230653.

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Vilmin, Stéphane. "Turbulence modeling on unstructured meshes for 3D turbomachinery CFD /." Lausanne : EPFL, 1998. http://library.epfl.ch/theses/?nr=1864.

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Spencer, Ronald Alex. "Analysis of High Fidelity Turbomachinery CFD Using Proper Orthogonal Decomposition." BYU ScholarsArchive, 2016. https://scholarsarchive.byu.edu/etd/5846.

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Assessing the impact of inlet flow distortion in turbomachinery is desired early in the design cycle. This thesis introduces and validates the use of methods based on the Proper Orthogonal Decomposition (POD) to analyze clean and 1/rev static pressure distortion simulation results at design and near stall operating condition. The value of POD comes in its ability to efficiently extract both quantitative and qualitative information about dominant spatial flow structures as well as information about temporal fluctuations in flow properties. Observation of the modes allowed qualitative identification of shock waves as well as quantification of their location and range of motion. Modal coefficients revealed the location of the passage shock at a given angular location. Distortion amplification and attenuation between rotors was also identified. A relationship was identified between how distortion manifests itself based on downstream conditions. POD provides an efficient means for extracting the most meaningful information from large CFD simulation data. Static pressure and axial velocity were analyzed to explore the flow physics of 3 rotors of a compressor with a distorted inlet. Based on the results of the analysis of static pressure using the POD modes, it was concluded that there was a decreased range of motion in passage shock oscillation. Analysis of axial velocity POD modes revealed the presence of a separated region on the low pressure surface of the blade which was most dynamic in rotor 1. The thickness of this structure decreased in the near stall operating condition. The general conclusion is made that as the fan approaches stall the apparent effects of distortion are lessened which leads to less variation in the operating condition. This is due to the change in operating condition placing the fan at a different position on the speedline such that distortion effects are less pronounced. POD modes of entropy flux were used to identify three distinct levels of entropy flux in the blade row passage. The separated region was the region with the highest entropy due to the irreversibilities associated with separation.

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Coppinger, Miles. "Aerodynamic performance of an industrial centrifugal compressor variable inlet guide vane system." Thesis, Loughborough University, 1999. https://dspace.lboro.ac.uk/2134/7263.

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Industrial centrifugal air compressors can require a combination of a large range of mass flow, high efficiency, constant pressure ratio, and constant rotational speed, specifically when used for sewage effluent aeration treatment. In order to achieve this performance it is common to use variable inlet guide vanes (VIGV's). The performance characteristics of an existing VIGV design have been determined using both an experimental test facility and state of art numerical techniques. The results obtained from these techniques are far more comprehensive than earlier fullscale performance testing. Validation of the performance of the existing design using these techniques has led to the development of a new vane design and potential improvements to the inlet ducting geometry. The aerodynamic interaction between the VIGV system and the centrifugal compressor impeller has also been investigated using a 3-D computational model of the complete variable geometry compressor stage. The results of these investigations have been validated by data available from full scale experimental testing. Strong correlation was obtained between numerical and experimental techniques, and a predicted improvement in polytropic efficiency up to 3% at low flow rates using the re-designed variable inlet guide vanes has been achieved. The overall outcome of this research is a usable VIGV design technique for real industrial compressor environments, and confirmation that an acceptable design can be achieved that represents a rewarding improvement in performance.

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Mouret, Gaëlle. "Adaptation of phase-lagged boundary conditions to large-eddy simulation in turbomachinery configuration." Phd thesis, Toulouse, INPT, 2016. http://oatao.univ-toulouse.fr/16497/7/Mouret_Gaelle_2016.pdf.

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The more and more restrictive standards in terms of fuel consumption and pollution for aircraft engines lead to a constant improvement of their design. Numerical simulations appear as an interesting tool for a better understanding and modeling of the turbulent phenomena which occur in turbomachinery. The large-eddy simulation (LES) of a turbomachinery stage at realistic conditions (Mach number, Reynolds number...) remains out of reach for industrial congurations. The phase-lagged method, widely used for unsteady Reynolds-averaged Navier--Stockes (URANS) calculations, is a good candidate to reduce the computational cost. However, it needs to store the signal at all the boundaries over a full passage of the opposite blade. A direct storage of the information being excluded given the size of the mesh grid and timesteps involved, the most used solution currently is to decompose the signal into Fourier series. This solution retains the fundamental frequency of the signal (the opposite blade passage frequency) and a limited number of harmonics. In the frame of a LES, as the spectra are broadband, it implies a loss of energy. Replacing the Fourier series decomposition by a proper orthogonal decomposition (POD) allows the storage of the signal at the interfaces without making any assumptions on the frequency content of the signal, and helps to reduce the loss of energy caused by the phase lagged method. The compression is done by removing the smallest singular values and the associated vectors. This new method is first validated on the URANS simulations of turbomachinery stages and compared with Fourier series-based conditions and references calculations with multiple blades per row. It is then applied to the large eddy simulation of the flow around a cylinder. The error caused by the phase-lagged assumption and compression are separated and it is showed that the use of the POD allows to halve the filtering of the velocity fluctuations with respect to the Fourier series, for a given compression rate. Finally, the large eddy simulation of a compressor stage with POD phase-lagged conditions is carried out to validate the method for realistic turbomachinery configurations.

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Campos, André Perpignan Viviani de. "Desenvolvimento de um compressor radial para turbina a gás de pequeno porte." Universidade de São Paulo, 2013. http://www.teses.usp.br/teses/disponiveis/3/3150/tde-24122013-111621/.

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O desenvolvimento de tecnologia na área de turbomáquinas é essencial ao desenvolvimento da indústria nacional e o Laboratório de Engenharia Ambiental e Térmica da Escola Politécnica da Universidade de São Paulo tem compreendido ações para este propósito. Este trabalho tem por objetivo desenvolver um compressor para uma turbina a gás de pequeno porte de 500 kW, primeiro passo para o projeto e construção da turbina como um todo. A partir da análise do ciclo termodinâmico e da análise de adimensionais, o tipo de compressor a ser utilizado foi determinado. Optou-se pelo projeto de um compressor centrífugo. Iniciou-se o projeto através de análise e correlações unidimensionais com previsão de desempenho, definindo algumas geometrias iniciais a serem avaliadas nas fases seguintes. Realizou-se a análise bidimensional do impelidor com a ferramenta computacional Vista TF que utiliza o método de curvatura de linhas de corrente. Por fim, a geometria tridimensional foi definida com uso de simulações de dinâmica de fluidos computacional. De acordo com as simulações, o compressor projetado tem desempenho condizente com os requisitos impostos.
Technology development in turbomachinery is essential to the national industry development and the Laboratory of Environmental and Thermal Engineering of the Polytechnic School of the University of São Paulo is engaged on this purpose. This work intends to design a compressor for a small 500 kW gas turbine, the first step in the whole turbine design and construction. The compressor type was determined from thermodynamical cycle and adimensional analysis. The centrifugal type compressor was chosen. The design was initialized using one-dimensional analysis and correlations with performance prediction models, defining initial geometries to be evaluated in the upcoming design phases. The impeller was analyzed with a two dimensional computational tool named Vista TF, which uses the streamline curvature method. The tridimensional geometry was defined using computational fluid dynamics. According to the simulations, the design compressor performs satisfying the imposed requirements.

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GUIDOTTI, EMANUELE. "Analysis of the Unsteady Flow in an Aspirated Counter-Rotating Compressor Using the Nonlinear Harmonic Balance Method." University of Cincinnati / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1218690946.

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Giuliani, James Edward. "Jet Engine Fan Response to Inlet Distortions Generated by Ingesting Boundary Layer Flow." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1468564279.

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Gezguc, Cagri. "Compressor Tandem Blade Aerothermodynamic Performance Evaluation Using Cfd." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614707/index.pdf.

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In this study, loss and loading characteristics of compressor tandem blades are evaluated. Whole study was focused on change of the total camber so called turning angle. Effects of camber change were investigated in terms of loss and loading characteristics. Methodology was increasing overall camber first by aligning angular positions of blades and second, if required, using more cambered airfoils. 2-dimensional cascade flow CFD analyses were performed to obtain loss-loading information of different tandem blade combinations. Acquired results were compared with the classical axial compressor blades&rsquo
loading and loss characteristics which were obtained from literature. Results showed that most of the time tandem blade configuration performed better than the single blade counterpart in 2-dimensional cascade flow. Lastly, to clarify the benefit of the study and present the gained performance in numbers, only one cascade flow CFD analysis was performed for a classical single compressor blade. Loss and loading results were compared with the tandem blade counterpart where single and tandem configurations both having the same degree of camber. It was clearly seen that tandem blade performed better again.

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Lockwood, C. "Comparison of average-passage equation closures through simulation of single and multi-row axial compressors : the limitations of using a commercial CFD code." Thesis, Cranfield University, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.323824.

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Books on the topic "Turbomachinery; CFD"

1

North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Turbomachinery design using CFD. Neuilly sur Seine, France: AGARD, 1994.

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Advisory Group for Aerospace Research and Development. Consultant and Exchange Programme. and Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel., eds. Turbomachinery design using CFD. Neuilly sur Seine: Agard, 1994.

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A, Blech Richard, and United States. National Aeronautics and Space Administration., eds. Turbomachinery CFD on parallel computers. [Washington, DC: National Aeronautics and Space Administration, 1992.

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Aissa, Mohamed Hassanine. GPU-accelerated CFD Simulations for Turbomachinery Design Optimization. von Karman Institute for Fluid Dynamics, 2018. http://dx.doi.org/10.35294/phdt201801.

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United States. National Aeronautics and Space Administration., ed. The development of scalable parallel 3-D CFD algorithm for turbomachinery. [Mississippi State, Miss.]: Mississippi State University, 1993.

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The development of scalable parallel 3-D CFD algorithm for turbomachinery. [Mississippi State, Miss.]: Mississippi State University, 1993.

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TADS, a CFD-based turbomachinery and analysis design system with GUI. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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A, Myers R., Delaney R. A, and United States. National Aeronautics and Space Administration., eds. TADS, a CFD-based turbomachinery and analysis design system with GUI. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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A, Myers R., Delaney Robert A, and United States. National Aeronautics and Space Administration., eds. TADS, a CFD-based turbomachinery and analysis design system with GUI. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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A, Suresh, and Lewis Research Center, eds. Analysis of inlet-compressor acoustic interactions using coupled CFD codes. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Book chapters on the topic "Turbomachinery; CFD"

1

Montomoli, Francesco, Mauro Carnevale, Antonio D’Ammaro, Michela Massini, and Simone Salvadori. "Limitations in Turbomachinery CFD." In Uncertainty Quantification in Computational Fluid Dynamics and Aircraft Engines, 21–32. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-14681-2_2.

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Wiedermann, Alexander. "CFD for Turbomachinery Blading Analysis and Design." In Advances in Fluid Mechanics and Turbomachinery, 29–38. Berlin, Heidelberg: Springer Berlin Heidelberg, 1998. http://dx.doi.org/10.1007/978-3-642-72157-1_3.

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Ilieva, Galina. "CFD—A Powerful Visualization Tool in Turbomachinery Applications." In Lecture Notes in Mechanical Engineering, 283–305. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-9806-3_10.

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Namba, M., N. Yamasaki, and T. Otsuka. "Comparison of DLT And CFD Predictions of Unsteady Aerodynamic Force on Vibrating Supersonic Through-Flow Fan Cascade." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 831–45. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_54.

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Xu, C., and R. S. Amano. "3 CFD for industrial turbomachinery design." In Computational Fluid Dynamics and Heat Transfer, 61–126. WIT Press, 2010. http://dx.doi.org/10.2495/978-1-84564-144-3/03.

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Lee, Yu-Tai, Thomas W. Bein, Chunill Hah, James Loellbach, Jinzhang Feng, and Charles L. Merkle. "CFD Research on Axial-Flow Turbomachinery." In Turbomachinery Fluid Dynamics and Heat Transfer, 253–75. Routledge, 2017. http://dx.doi.org/10.1201/9780203734919-12.

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Mori, Masaaki. "Wake-Body Interaction Noise Simulated by the Coupling Method Using CFD and BEM." In Vortex Dynamics Theories and Applications. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.92783.

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In many engineering applications, obstacles often appear in the wake of obstacles. Vortices shed from an upstream obstacle interact with downstream obstacle and generate noise, for example blades in a turbomachinery, tubes in a heat exchanger, rotating blades like a helicopter and wind turbine and so on. This phenomenon is called wake-body interaction or body-vortex interaction (BVI). The rod-airfoil and airfoil-airfoil configurations are typical models for the wake-body interaction. A rod and an airfoil are immersed upstream of the airfoil. In this chapter, we review the noise mechanism generated by the wake-body interaction and show the numerical results obtained by the coupling method using commercial CFD and acoustic BEM codes. The results show that depending on the spacing between the rod or airfoil and the airfoil, the flow patterns and noise radiation vary. With small spacing, the vortex shedding from the upstream obstacle is suppressed and it results in the suppression of the sound generation. With large spacing, the shear layer or the vortices shed from the upstream obstacle impinge on the downstream obstacle and it results in the large sound generation. The dominant peak frequency of the generated sound varies with increase in the spacing between the two obstacles.

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DAIGUJI, Hisaaki. "PROGRESS IN CFD FOR TURBOMACHINE CASCADE FLOW PROBLEMS EMPHASIZING INVESTIGATIONS IN JAPAN." In Computational Fluid Dynamics Review 1998, 12–41. WORLD SCIENTIFIC, 1998. http://dx.doi.org/10.1142/9789812812957_0002.

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Müller, L., J. D. Müller, and T. Verstrate. "CAD-based multidisciplinary optimization of turbomachinery components by gradient-based methods." In VKI Lecture Series. von Karman Institute for Fluid Dynamics, 2018. http://dx.doi.org/10.35294/ls201804.muller3.

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Conference papers on the topic "Turbomachinery; CFD"

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Denton, John D. "Some Limitations of Turbomachinery CFD." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22540.

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CFD is now an essential tool for the design of all types of turbomachinery. However, as engineers are exposed more and more to the results of CFD and less and less to experimental data there is a danger that they may not realise the limitations of CFD and so will view its predictions as more reliable than they really are and not question them sufficiently. This is particularly dangerous when CFD is use as part of an optimisation procedure. The objective of this paper is to try to expose some of the limitations of CFD as used for routine turbomachinery design. CFD is not an exact science. Errors can arise from the following sources: • Numerical errors due to finite difference approximations. • Modeling errors, where the true physics is not known or is too complex to model — e.g. turbulence modeling. • Unknown boundary conditions, such as inlet pressure or temperature profiles. • Unknown geometry such as tip clearances or leading edge shapes. • Assumption of steady flow. Each of these sources of error is discussed and examples of the differences they can cause in the predictions are shown. Despite these limitations CFD remains an extremely valuable tool for turbomachinery design but it should be used on a comparative basis and not trusted to give quantitative predictions of performance.

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Moore, Joan G., and John Moore. "Realizability in Turbulence Modelling for Turbomachinery CFD." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-024.

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It is obvious that the Reynolds normal stresses uu¯ should always be positive in all directions, i.e. the computed turbulence stresses should be realizable. However, the commonly used two-equation turbulence models do not incorporate realizability. They take the turbulent viscosity as cμk2/ε with cμ a constant, and frequently generate negative normal stresses far from walls in the nominally inviscid sections of turbomachinery flows. Pressure gradients due to leading edge stagnation and blade turning create an inviscid strain field. These strains cause the calculation of negative normal stresses over significant portions of the flow field. The result can be erroneous increases in turbulence kinetic energy upstream of the leading edge by a factor of ten or more. This erroneous turbulence is then convected around the blade and through the blade row, significantly affecting the computed boundary layer development and profile losses. Frequently the problem of overproduction is avoided by using artificially high values of the dissipation, ε, at the inlet. But this incorrect procedure is not needed when realizability is incorporated in the turbulence model. The paper reviews some methods and models which ensure realizability in two-equation turbulence models. The extent of the problem and its solution are illustrated with examples from compressor and turbine cascades.

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THOMAS, MATTHEW, NANCY SHIMP, MICHAEL RAW, PAUL GALPIN, and GEORGE RAITHBY. "The development of an efficient turbomachinery CFD analysis procedure." In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2394.

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Northall, John D. "The Influence of Variable Gas Properties on Turbomachinery CFD." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68478.

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This paper describes the inclusion of variable gas properties within a Reynolds average Navier-Stokes solver for turbomachinery and its application to multi-stage turbines. Most current turbomachinery CFD models the gas as perfect with constant specific heats. However, the specific heat at constant pressure, CP, can vary significantly. This is most marked in the turbine where large variations of temperature are combined with variations in the fuel air ratio. In the current model CP is computed as a function of the local temperature and fuel air ratio using polynomial curve fits to represent the real gas behaviour. The importance of variable gas properties is assessed by analysing a multi-stage turbine typical of the core stages of a modern aero-engine. This calculation includes large temperature variations due to radial profiles at inlet, the addition of cooling air and work extraction through the machine. The calculation also includes local variations in fuel-air ratio resulting from the inlet profile and the dilution of the mixture by the addition of coolant air. A range of gas models is evaluated. The addition of variable gas properties is shown to have no significant effect on the convergence of the algorithm, and the extra computational costs are modest. The models are compared with emphasis on the parameters of importance in turbine design, such as capacity, work and efficiency.

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Kielb, Robert. "CFD for turbomachinery unsteady flows - An aeroelastic design perspective." In 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-429.

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Gu, Fahua, and Mark R. Anderson. "CFD-Based Throughflow Solver in a Turbomachinery Design System." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27389.

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Throughflow analysis is a critical component for the multi-stage axial turbomachine design. The Euler throughflow approach has been developed over the last couple of decades, but has been less successful than its early peer, the streamline curvature approach. In this paper an Euler throughflow approach is described for engineering applications. It includes the steps needed to construct the stream surface, such as modifications for the incidence and deviation, and the throat area correction. The flow angle difference at the trailing edge and in the downstream non-bladed gap stations is resolved, and the numerical loss from solving the Euler equation is removed as well. This solver has been integrated into a comprehensive turbomachinery design system. It creates and modifies the machine geometries and predicts the machine performance at different levels of approximation, including one-dimensional design and analysis, quasi-three-dimensional methods (blade-to-blade and throughflow) and full-three-dimensional steady-state CFD analysis. The flow injection and extraction functions are described, as is the implementation of the radial mass distribution. Some discussion is dedicated to the shock calculation. Finally, examples are provided to demonstrate the pros and cons of the Euler throughflow approach and also to demonstrate the potential to solve for a wider range of flow conditions, particularly choked and transonic flows that limit stream function based solvers.

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Denton, John D. "Multall: An Open Source, CFD Based, Turbomachinery Design System." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63993.

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Turbomachinery design systems are usually the jealously guarded property of large companies, the author is not aware of any for which the source code is freely available. The present paper is aimed providing a freely available system that can be used by individuals or small companies who do not have access to an in-house system. The design system is based on the 3D CFD solver Multall, which has been developed over many years. Multall can obtain solutions for individual blade rows or for multi-stage machines, it can also perform quasi-3D blade-to-blade calculations on a prescribed stream surface and axisymmetric throughflow calculations. Multall is combined with a one-dimensional mean-line program, Meangen, which predicts the blading parameters on a mean stream surface and writes an input file for Stagen. Stagen is a blade geometry generation and manipulation program which generates and stacks the blading, combines it into stages, and writes an input file for Multall. The system can be used to design the main blade path of all types of turbomachines. Although it cannot design complex features such as shroud seals and individual cooling holes these features can be modeled and their effect on overall performance predicted. The system is intended to be as simple and easy to use as possible and the solver is also very fast compared to most CFD codes. A great deal of user experience ensures that the overall performance is reasonably well predicted for a wide variety of machines. This paper describes the system in outline and gives an example of its use. The source codes are written in FORTRAN77 and are freely available for other users to try.

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Novak, O., O. Schäfer, B. Schönung, and H. Pätzold. "Use of Advanced CFD Codes in the Turbomachinery Design Process." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-324.

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This paper describes the development and application of CFD codes, based on time-marching finite-volume formulations to the flow analysis in blade cascades, blade rows and stages of modern turbomachines. Special attention is paid to the reduction of the numerical dissipation of finite-volume discretization schemes, the numerical simulation of shock waves and to viscous effects. Furthermore, the application of solution-adaptive structured and unstructured computational grids is investigated. Finally, the ability of time-marching finite-volume methods to simulate three-dimensional flow effects in turbomachinery bladings is demonstrated.

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Wyman, Nicholas J., Paul Galpin, Thorsten Hansen, and Georg Scheuerer. "Robust, Efficient and Accurate Mesh Adaptation for Turbomachinery CFD Simulations." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3688.

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Jasak, Hrvoje, and Martin Beaudoin. "OpenFOAM Turbo Tools: From General Purpose CFD to Turbomachinery Simulations." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-05015.

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OpenFOAM is an established object-oriented library for Computational Continuum Mechanics, with emphasis on CFD. It implements physical models of fluid flow, structural analysis, heat and mass transfer using equation mimicking, with unstructured polyhedral mesh support and massive parallelism in domain decomposition mode. In order to use OpenFOAM in turbomachinery CFD, its “general purpose” capabilities are enhanced with turbo-specific features, related to physics of rotating regions and rotor-stator interfaces. Handling for geometric simplifications of multi-blade and multi-stage rotating machines are implemented, including simple stage interfaces, non-equal pitch of blade passages, pitch-wise cyclicity and mixing plane averaging. In this paper we describe the implementation of turbomachinery-specific features in OpenFOAM, in the spirit of object orientation and C++. Emphasis is given to the basic functionality of turbo tools, software layout in OpenFOAM, numerical formulation of stage interfaces and their place in overall code design. The paper is concluded with examples of turbomachinery simulations, illustrating the capability of turbo tools on industrial cases of incompressible and compressible turbomachinery flows.

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