Bibliografías temáticas / Meanline design

Literatura académica sobre el tema "Meanline design"

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Publicado: 6 de septiembre de 2023

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Artículos de revistas sobre el tema "Meanline design"

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Biba, Yuri y Peter Menegay. "Inverse Design of Centrifugal Compressor Stages Using a Meanline Approach". International Journal of Rotating Machinery 10, n.º 1 (1 de enero de 2004): 75–84. http://dx.doi.org/10.1080/10236210490258106.

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Biba, Yuri y Peter Menegay. "Inverse Design of Centrifugal Compressor Stages Using a Meanline Approach". International Journal of Rotating Machinery 10, n.º 1 (2004): 75–84. http://dx.doi.org/10.1155/s1023621x04000089.

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This article discusses an approach for determining meanline geometric parameters of centrifugal compressor stages given specified performance requirements. This is commonly known as the inverse design approach. The opposite process, that of calculating performance parameters based on geometry input is usually called analysis, or direct calculation. An algorithm and computer code implementing the inverse approach is described. As an alternative to commercially available inverse design codes, this tool is intended for exclusive OEM use and calls a trusted database of loss models for individual stage components, such as impellers, guide vanes, diffusers, etc. The algorithm extends applicability of the inverse design code by ensuring energy conservation for any working medium, like imperfect gases. The concept of loss coefficient for rotating impellers is introduced for improved loss modelling. The governing conservation equations for each component of a stage are presented, and then described in terms of an iterative procedure which calculates the required one-dimensional geometry. A graphical user interface which facilitates user input and presentation of results is discussed briefly. The object-oriented nature of the code is highlighted as a platform which easily provides for maintainability and future extensions.
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Bahamonde, Sebastian, Matteo Pini, Carlo De Servi y Piero Colonna. "Active subspaces for the optimal meanline design of unconventional turbomachinery". Applied Thermal Engineering 127 (diciembre de 2017): 1108–18. http://dx.doi.org/10.1016/j.applthermaleng.2017.08.093.

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Cho, Soo-Yong, Bum-Seog Choi y Hyung-Soo Lim. "Off-Design Performance Analysis of a 7 MW Class Steam Turbine by Meanline Analysis". Journal of Power System Engineering 24, n.º 2 (30 de abril de 2020): 5–14. http://dx.doi.org/10.9726/kspse.2020.24.2.005.

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Lee, Sangkyoung y Hal Gurgenci. "A comparison of three methodological approaches for meanline design of supercritical CO2 radial inflow turbines". Energy Conversion and Management 206 (febrero de 2020): 112500. http://dx.doi.org/10.1016/j.enconman.2020.112500.

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Deligant, Michael, Moritz Huebel, Tchable-Nan Djaname, Florent Ravelet, Mathieu Specklin y Mohamed Kebdani. "Design and off-design system simulation of concentrated solar super-critical CO2 cycle integrating a radial turbine meanline model". Energy Reports 8 (noviembre de 2022): 1381–93. http://dx.doi.org/10.1016/j.egyr.2022.07.141.

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Bahamonde, Sebastian, Matteo Pini, Carlo De Servi, Jürg Schiffmann y Piero Colonna. "Corrigendum to “Active subspaces for the optimal meanline design of unconventional turbomachinery” [Appl. Therm. Eng. 127 (2017) 1108–1118]". Applied Thermal Engineering 150 (marzo de 2019): 1353–55. http://dx.doi.org/10.1016/j.applthermaleng.2018.12.099.

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Jung, Hyung-Chul y Susan Krumdieck. "Meanline design of a 250 kW radial inflow turbine stage using R245fa working fluid and waste heat from a refinery process". Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 230, n.º 4 (10 de marzo de 2016): 402–14. http://dx.doi.org/10.1177/0957650916637966.

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Alawadhi, Khaled, Yousef Alhouli, Ali Ashour y Abdullah Alfalah. "Design and Optimization of a Radial Turbine to Be Used in a Rankine Cycle Operating with an OTEC System". Journal of Marine Science and Engineering 8, n.º 11 (29 de octubre de 2020): 855. http://dx.doi.org/10.3390/jmse8110855.

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Design and optimization of a radial turbine for a Rankine cycle were accomplished ensuring higher thermal efficiency of the system despite the low turbine inlet temperature. A turbine design code (TDC) based on the meanline design methodology was developed to construct the base design of the turbine rotor. Best design practices for the base design were discussed and adopted to initiate a robust optimization procedure. The baseline design was optimized using the response surface methodology and by coupling it with the genetic algorithm. The design variables considered for the study are rotational speed, total to static speed ratio, hub radius ratio, shroud radius ration, and number of blades. Various designs of the turbine were constructed based on the Central Composite Design (CCD) while performance variables were computed using the in-house turbine design code (TDC) in the MATLAB environment. The TDC can access the properties of the working fluid through a subroutine that links NIST’s REFPROP to the design code through a subroutine. The finalization of the geometry was made through an iterative process between 3D-Reynolds-Averaged Navier-Stokes (RANS) simulations and the one-dimensional optimization procedure. 3D RANS simulations were also conducted to analyze the optimized geometry of the turbine rotor for off-design conditions. For computational fluid dynamics (CFD) simulation, a commercial code ANSYS-CFX was employed. 3D geometry was constructed using ASYS Bladegen while structured mesh was generated using ANSYS Turbogrid. Fluid properties were supplied to the CFD solver through a real gas property (RGP) file that was constructed in MATLAB by linking it to REFPROP. Computed results show that an initial good design can reduce the time and computational efforts necessary to reach an optimal design successfully. Furthermore, it can be inferred from the CFD calculation that Response Surface Methodology (RSM) employing CFD as a model evaluation tool can be highly effective for the design and optimization of turbomachinery.
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Large, James y Apostolos Pesyridis. "Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems". Aerospace 6, n.º 5 (14 de mayo de 2019): 55. http://dx.doi.org/10.3390/aerospace6050055.

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In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the concept of converting existing micro turbojet engines into turbofans with the use of a continuously variable gearbox, thus maintaining a single spool configuration and relative design simplicity. This is an effort to reduce the initial engine development cost, whilst improving the propulsive performance. The BMT 120 KS micro turbojet engine is selected for the performance evaluation of the conversion process using the gas turbine performance software GasTurb13. The preliminary design of a matched low-pressure compressor (LPC) for the proposed engine is then performed using meanline calculation methods. According to the analysis that is carried out, an improvement in the converted micro gas turbine engine performance, in terms of thrust and specific fuel consumption is achieved. Furthermore, with the introduction of a CVT gearbox, the fan speed operation may be adjusted independently of the core, allowing an increased thrust generation or better fuel consumption. This therefore enables a wider gamut of operating conditions and enhances the performance and scope of the tactical UAV.
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Tesis sobre el tema "Meanline design"

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Birkenheier, David Andrew. "Non-uniform radial meanline method for off-design performance estimation of multistage axial compressors". Thesis, Massachusetts Institute of Technology, 2018. http://hdl.handle.net/1721.1/119062.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2018.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 111-112).
The increasing use of renewable energy sources necessitates power-generating gas turbines capable of frequently and rapidly starting up to supplement the energy supply when renewable sources alone cannot meet demand [1], [21. This makes the off-design performance of such gas turbines more important as they spend more of their operational life off the design point. Currently off-design performance cannot be estimated with high fidelity until late in the gas turbine compressor design process at which point the design is largely fixed and only limited changes can be made. This thesis presents a Non-Uniform Radial Meanline method for multistage axial compressor off-design performance estimation, capturing the transfer of radial flow non-uniformity and its impact on compressor blade row performance. This method enables the high-fidelity characterization of blade row performance and the stage matching of multistage compressors with non-uniformity effects included. A new representation of non-uniform radial flow profiles using orthonormal basis functions was developed to provide a compact representation suitable for inclusion in a one-dimensional performance estimation method. The link between radial flow non-uniformity and compressor blade row performance was characterized using three-dimensional embedded stage calculations. An initial implementation of the Non-Uniform Radial Meanline method was demonstrated for different compressor inlet non-uniformities. The computations show that the new approach provides an effective means of incorporating radial flow non-uniformity into a one-dimensional compressor performance estimation method.
by David Andrew Birkenheier.
S.M.
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Muppana, Sai. "Multi-fidelity Design and Analysis of Single Hub Multi-rotor High Pressure Centrifugal Compressor". University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1553517075653458.

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Symes, Richard. "Design and modelling of a heat recovery cycle and turbine for a low temperature hydrogen fuel cell". Thesis, Queensland University of Technology, 2021. https://eprints.qut.edu.au/213827/1/Richard_Symes_Thesis.pdf.

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This thesis examines the viability of waste heat recovery from a small scale, low temperature hydrogen fuel cell, to generate additional power using a thermodynamic cycle and micro-turbine. It investigates the optimal fluid selection for an organic Rankine cycle and models a radial inflow turbine to generate power from the cycle, which was able to improve the efficiency of the fuel cell by 5%. This work optimises the cycle and turbine designs to match the operating conditions and achieve the highest efficiency and validates the result using 3D fluid simulations.
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Actas de conferencias sobre el tema "Meanline design"

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Zhdanov, Ivan, Stephan Staudacher y Sergey Falaleev. "An Advanced Usage of Meanline Loss Systems for Axial Turbine Design Optimisation". En ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94323.

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A comprehensive axial turbine framework model has been developed at the Institute of Aircraft Propulsion Systems, University of Stuttgart. It discovers the principles of a meanline optimisation and shows its advantages for quick prediction of optimal meanline parameters considering manufacturing, mechanical and aerodynamic requirements. The framework model can incorporate different loss correlations and compare their results for one and the same multi-dimensional design parameter space. A special attention is paid to the influence of loss correlations on optimal values of meanline parameters. It is shown that, although all loss correlation has their own global optimum of turbine performance in the multi-dimensional design parameter space, they are going to coincide if the requirements addressed to a turbine are considered and the turbine design constraints, e.g. a specified rotational speed, inlet diameter and etc., are applied. Thus, the more constraints in the design parameter space exist, the lower the impact of a loss correlation on optimal values of meanline parameters.
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Lizarraga, Giovanni y Pedro Perez. "Preliminary Meanline Design for Gas Turbines Using Multi-objective Optimization". En 2010 Ninth Mexican International Conference on Artificial Intelligence (MICAI). IEEE, 2010. http://dx.doi.org/10.1109/micai.2010.18.

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Unglaube, Tina y Hsiao-Wei D. Chiang. "Small Scale Supercritical CO2 Radial Inflow Turbine Meanline Design Considerations". En ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75356.

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In recent years closed loop supercritical carbon dioxide Brayton cycles have drawn the attention of many researchers as they are characterized by a higher theoretic efficiency and smaller turbomachinery size compared to the conventional steam Rankine cycle for power generation. Currently, first prototypes of this emerging technology are under development and thus small scale sCO2 turbomachinery needs to be developed. However, the design of sCO2 turbines faces several new challenges, such as the very high rotational speed and the high power density. Thus, the eligibility of well-established radial inflow gas turbine design principles has to be reviewed regarding their suitability for sCO2 turbines. Therefore, this work reviews different suggestion for optimum velocity ratios for gas turbines and aims to re-establish it for sCO2 turbines. A mean line design procedure is developed to obtain the geometric dimensions for small scale sCO2 radial inflow turbines. By varying the specific speed and the velocity ratio, different turbine configurations are set up. They are compared numerically by means of CFD analysis to conclude on optimum design parameters with regard to maximum total-to-static efficiency. Six sets of simulations with different specific speeds between 0.15 and 0.52 are set up. Higher specific speeds could not be analyzed, as they require very high rotational speeds (more than 140k RPM) for small scale sCO2 turbines (up to 150kWe). For each set of simulations, the velocity ratio that effectuates maximum efficiency is identified and compared to the optimum parameters recommended for radial inflow turbines using subcritical air as the working fluid. It is found that the values for optimum velocity ratios suggested by Rohlik (1968) are rather far away from the optimum values indicated by the conducted simulations. However, the optimum values suggested by Aungier (2005), although also established for subcritical gas turbines, show an approximate agreement with the simulation results for sCO2 turbines. Though, this agreement should be studied for a wider range of specific speeds and a finer resolution of velocity ratios. Furthermore, for high specific speeds in combination with high velocity ratios, the pressure drop of the designed turbines is too high, so that the outlet pressure is beyond the critical point. For low specific speeds in combination with low velocity ratios, the power output of the designed turbines becomes very small. Geometrically, turbines with low specific speeds and high velocity ratios are characterized by very small blade heights, turbines with high specific speeds and small velocity ratios by very small diameters.
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Hu, Zongjun, Gecheng Zha, Matthew Montgomery, Thomas Roecken y John Orosa. "Transonic Compressor Rotor Design Using Non-Monotonic Meanline Angle Distribution". En ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27994.

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A non-monotonic meanline angle distribution technique with local negative camber is applied to a transonic rotor blade from the hub area to tip with the inlet Mach number varying from subsonic to low supersonic. The blade passage area is controlled by the non-monotonic meanline angle distribution, which results in reduced peak Mach number and weakened or removed shock wave. The negative camber is used downstream of the throat and hence it does not affect the flow passing capability of the blade section. The design point efficiency is significantly increased and the stall margin at part speed is also improved. Detailed results are given in the paper.
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Qiu, Xuwen, Eric M. Krivitzky y Peter Bollweg. "Meanline Modeling of Ported Shroud Turbocharger Compressor". En ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68915.

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The requirements for higher fuel economy and better diesel and gasoline engines demand a wider range in turbocharger compressor operation. Ported shroud compressor housing is one of the most commonly used techniques for compressor map width enhancement. Although the general mechanism of such a flow feature is well understood, there are no readily available design tools to guide the engineers at the preliminary design stage. Designers have had to rely on three-dimensional (3D) CFD tools to sort out many design variables, but these tools can be prohibitively expensive. This paper explains how to develop a ported shroud compressor model on top of a commercial meanline compressor design program. The model considers some basic parameters, such as bleed location and geometry, which drive the recirculation or bypass flow through the bleed channel. The effects of the secondary flow on the compressor performance, such as pressure rise, efficiency, and stall and choke margins are also analyzed. The model prediction is validated with CFD simulation and test data.
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Lee, Sangkyoung, David Mee, Zhiqiang Guan y Hal Gurgenci. "Meanline Design and Off-Design Performance Prediction for Supercritical CO2 Radial Inflow Turbines". En 22nd Australasian Fluid Mechanics Conference AFMC2020. Brisbane, Australia: The University of Queensland, 2020. http://dx.doi.org/10.14264/6ce0260.

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Hohenberg, Karl, Ricardo Martinez-Botas, Piotr Łuczyński, Carola Freytag y Manfred Wirsum. "Numerical and Experimental Investigation of a Low Order Radial Turbine Model for Engine-Level Optimisation of Turbocharger Design". En ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15698.

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Abstract This paper presents the development and validation of a meanline model by means of numerical and experimental methods, to determine it’s feasibility as an optimisation tool for turbocharger matching. Using a parametric turbine model, numerical experiments were conducted accounting for variations of several key turbine design parameters and a wide operating range. The resulting dataset was used to test the accuracy of the meanline model when calibrated to a baseline design and thus evaluate it’s ability of extrapolating to different designs. The loss models were examined in more detail, and a set of loss models which provided the most accurate results is presented. The meanline model was further validated experimentally using dynamometer test results of 6 turbine designs from the same parametric turbine model. The result showed that for design point and high power operation, an error of less than 3.1% and 2.0% was achieved for efficiency and mass flow parameter respectively. This led to the conclusion that the model would be sufficiently accurate to represent design changes relevant to turbocharger matching.
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Oh, JongSik. "Investigation of Off-Design Performance of Vaned Diffusers in Centrifugal Compressors: Part I — A Channel-Wedge Diffuser". En ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30387.

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Experimental and numerical investigations of the off-design performance of a simple channel-wedge diffuser in a small centrifugal compressor are presented. Surge and choke conditions as well as design point are considered using somewhat limited range of experimental data and also supplementary 3D CFD results. Some critical meanline design parameters’ behavior is investigated numerically, to render the basis for improved modelings in the meanline performance prediction.
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Qiu, Xuwen, David Japikse y Mark Anderson. "A Meanline Model for Impeller Flow Recirculation". En ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-51349.

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Flow recirculation at the impeller inlet and outlet is an important feature that affects impeller performance, especially the power consumption at a very low flow rate. Although the mechanisms for this flow phenomenon have been studied, a practical model is needed for meanline modeling of impeller off-design performance. In this paper, a meanline recirculation model is proposed. At the inlet, the recirculation zone acts as area blockage to relieve the large incidence of the active flow at a low flow rate. The size of the blockage is estimated through a critical area ratio of an artificial “inlet diffuser” from the inlet to throat. The intensity of the reverse flow can then be calculated by assuming a linear velocity profile of meridional velocity in the recirculation zone. At the impeller outlet, a recirculation zone near the suction surface is established to balance the velocity difference on the pressure and suction sides of the blade. The size and the intensity of the outlet recirculation zone is assumed related to blade loading, which can be evaluated based on flow turning and Coriolis force. A few validation cases are presented showing a good comparison between test data and prediction by the model.
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Singh, Ambrish y Nand Kumar Singh. "Parametric Study and Meanline Design of Multistage Axial Flow Compressor for Process Application". En ASME 2015 Gas Turbine India Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gtindia2015-1341.

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An industrial axial compressor has to meet a wide range of operation requirements. These machines have to run continuously for four to five years before going for overhaul. Hence, overall high level of efficiency may be slightly relaxed to meet this requirement. This requires axial flow compressor design to be more conservative and flexible to accommodate changes required for process industry through modern design & development approaches. This paper deals with finding of optimum flow path configuration that will allow a successful detailed design to follow. The effect of various parameters such as hub to tip ratio, proper selection of design rpm, reactions, work coefficient & flow coefficient has been investigated and selected for optimal performance of the machine. Last stage of the compressor is selected as radial stage with the advantage of reduction in axial length and to provide radial outlet, which is more suitable outlet configuration. Meanline design and streamline analysis for each configuration is determined to find out good operating range (stall-free operation) before starting the detailed design.
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