Статті в журналах: "Turbomachines Design and construction"

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Żywica, Grzegorz, Tomasz Kaczmarczyk, Eugeniusz Ihnatowicz, Paweł Bagiński, and Artur Andrearczyk. "Design and Manufacturing of Micro-Turbomachinery Components with Application of Heat Resistant Plastics." Mechanics and Mechanical Engineering 22, no. 2 (August 24, 2020): 649–60. http://dx.doi.org/10.2478/mme-2018-0051.

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AbstractThe article discusses issues associated with the use of modern plastics for the construction of high-speed fluid-flow machines. Currently available plastics exhibit high chemical resistance as well as dimensional and shape stability across a wide temperature range. This allows them to be used for manufacturing components of micro turbomachinery, thereby reducing production time and costs. This article discusses the criteria for the selection of plastics suitable for a particular machine, namely micro turbogenerator operating in the organic Rankine cycle (ORC). In addition to the initial selection of materials based on their chemical and physical properties, strength calculations of selected turbogenerator subassemblies were carried out. The obtained results confirmed that some plastics can replace traditional materials used in the manufacture of ORC turbogenerators. This concerns, in particular, the components of the microturbine blade system. After the manufacture of a trial series of such components, it became apparent that, with appropriately chosen plastics, it is possible to shorten the machining time and reduce production costs, all while maintaining the required dimensional tolerances. The results obtained so far prove that it is possible to use plastics to produce components of modern turbomachines, for instance, parts of high-speed microturbines that have to withstand high operating temperatures.

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Sazonov, Yuri A., Mikhail A. Mokhov, Inna V. Gryaznova, Victoria V. Voronova, Khoren A. Tumanyan, Mikhail A. Frankov, and Nikolay N. Balaka. "Computational Fluid Dynamics (CFD) Simulation of Mesh Jet Devices for Promising Energy-Saving Technologies." Civil Engineering Journal 8, no. 12 (December 1, 2022): 2749–67. http://dx.doi.org/10.28991/cej-2022-08-12-06.

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This paper discusses the development of mesh jet devices for hybrid turbines, including developing Euler's ideas, and considers a new patented version of a mesh jet device designed to create guiding devices for turbines. The research methods are based on simulations using CFD and additive technologies. An intermediate conclusion is that a new scientific direction for the study and creation of mesh jet control systems has been formed as part of developing Euler's ideas. Calculation methods showed possible improvements in the performance of jet devices, including the use of curved tubes proposed by Euler to create turbines. This study shows that at the nozzle or mixing chamber outlet, the jet can deflect by an angle from +180° to -180° within the geometric sphere. This study also shows that the scientific groundwork prepared by Euler is not yet fully understood. The ongoing research mainly focuses on creating multi-mode jet devices designed for control systems for mesh turbomachines. Here, power consumption from an external source can be reduced to save energy. Some results of ongoing studies can also be applied in other industries (for example, when creating hybrid propulsion systems or propulsors). The scientific novelty of this work consists of improving the design methodology of jet machinery and turbomachines. Doi: 10.28991/CEJ-2022-08-12-06 Full Text: PDF

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Sazonov, Yuri Appolonievich, Mikhail A. Mokhov, Inna Vladimirovna Gryaznova, Victoria Vasilievna Voronova, Khoren Arturovich Tumanyan, Mikhail Alexandrovich Frankov, and Nikolay Nikolaevich Balaka. "Designing Mesh Turbomachinery with the Development of Euler’s Ideas and Investigating Flow Distribution Characteristics." Civil Engineering Journal 8, no. 11 (November 1, 2022): 2598–627. http://dx.doi.org/10.28991/cej-2022-08-11-017.

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This research discusses developing an Euler turbine-based hybrid mesh turbomachinery. Within the framework of mechanical engineering science, turbomachinery classification and a novel method for mesh turbomachinery design were considered. In such a turbomachine, large blades are replaced by a set of smaller blades, which are interconnected to form flow channels in a mesh structure. Previous studies (and reasoning within the framework of inductive and deductive logic) showed that the jet mesh control system allows for operation with several flows simultaneously and provides a pulsed flow regime in flow channels. This provides new opportunities for expanding the control range and reducing the thermal load on the turbomachine blades. The novel method for performance evaluation was confirmed by the calculation: the possibility of implementing pulsed cooling of blades periodically washed by a hot working gas flow (at a temperature of 1000°C) and a cold gas flow (at a temperature of 20°C) was shown. The temperature of the blade walls remained 490–525°C. New results of ongoing research are focused on creating multi-mode turbomachinery that operates in complicated conditions, e.g., in offshore gas fields. Gas energy is lost and dissipated in the throttle at the mouth of each high-pressure well. Within the framework of ongoing research, the environmentally friendly net reservoir energy of high-pressure well gas should be rationally used for operating a booster compressor station. Here, the energy consumption from an external power source can be reduced by 50%, according to preliminary estimates. Doi: 10.28991/CEJ-2022-08-11-017 Full Text: PDF

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Silva, E. Raimunda da, R. G. R. Camacho, and N. M. Filho. "Global optimization based on metamodel construction app lied to design axial turbomachinery cascades using CFD." IOP Conference Series: Earth and Environmental Science 12 (August 1, 2010): 012095. http://dx.doi.org/10.1088/1755-1315/12/1/012095.

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Demelio, G. P., SM Camporeale, A. Castellano, F. Cupertino, and M. Torresi. "Design and construction of an offshore diffuser augmented wind turbine with a high efficiency alternator." IOP Conference Series: Materials Science and Engineering 1214, no. 1 (January 1, 2022): 012030. http://dx.doi.org/10.1088/1757-899x/1214/1/012030.

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Abstract This paper describes the design and the assembly of a new type of a ducted wind turbine with an electric power generator adopting permanent high coercive magnets embedded in the peripheral ring of the rotor. The nominal power is 20 kW, and the maximum diameter of the external duct is 9 meters. The project has been carried out within the Marine Energy Laboratory (MEL) funded by the Italian Ministry for Education, University and Research (MIUR) and collects the most advanced technologies of naval maritime engineering and combines them with energy and turbomachinery technologies. The presence of a divergent duct enables the interception of a greater air mass flow rate, allowing the reduction of the rotor diameter and the deflections of the blades; hence, at constant tip speed ratio, a higher rotational speed compared to conventional turbines and a better efficiency of the permanent magnet power generator.

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Korakianitis, T. "Prescribed-Curvature-Distribution Airfoils for the Preliminary Geometric Design of Axial-Turbomachinery Cascades." Journal of Turbomachinery 115, no. 2 (April 1, 1993): 325–33. http://dx.doi.org/10.1115/1.2929238.

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Blade surfaces with continuous curvature and continuous slope of curvature minimize the possibility of flow separation, lead to improved blade designs, and reduce the direct and inverse blade-design iterations for the selection of isolated airfoils and gas-turbine-blade cascades. A method for generating two-dimensional blade shapes is presented. The geometry near the trailing edge is specified by an analytic polynomial, the main portion of the blade surface is mapped using as input a prescribed surface-curvature distribution, and the leading edge is specified as a thickness distribution added to a construction line. This procedure is similar for the suction and pressure surfaces, and by specification it constructs continuous slope-of-curvature surfaces that result in smooth surface-Mach-number and surface-pressure distributions. The method can be used to generate subsonic or supersonic airfoils for compressors and turbines, or isolated airfoils. The resulting geometric shapes can be used as inputs to various blade-design sequences. It is shown that, with other cascade-design parameters being equal, increasing the stagger angle of turbine blades results in more front-loaded and thinner blades, and that there is an optimum stagger angle resulting in minimum wake thickness. The subsonic axial-turbine blade rows included for discussion in this paper have been designed by iterative modifications of the blade geometry to obtain a desirable velocity distribution. The blade-design method can be used to improve the aerodynamic and heat transfer performance of turbine cascades, and it can result in high-performance airfoils, even if using the direct method exclusively, in very few iterations.

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Korakianitis, T. "Hierarchical Development of Three Direct-Design Methods for Two-Dimensional Axial-Turbomachinery Cascades." Journal of Turbomachinery 115, no. 2 (April 1, 1993): 314–24. http://dx.doi.org/10.1115/1.2929237.

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The direct and inverse blade-design iterations for the selection of isolated airfoils and gas turbine blade cascades are enormously reduced if the initial blade shape has performance characteristics near the desirable ones. This paper presents the hierarchical development of three direct blade-design methods of increasing utility for generating two-dimensional blade shapes. The methods can be used to generate inputs to the direct- or inverse-blade-design sequences for subsonic or supersonic airfoils for compressors and turbines, or isolated airfoils. The examples included for illustration are typical modern turbine cascades, and they have been designed by the direct method exclusively. The first method specifies the airfoil shapes with analytical polynomials. It shows that continuous curvature and continuous slope of curvature are necessary conditions to minimize the possibility of flow separation, and to lead to improved blade designs. The second method specifies the airfoil shapes with parametric fourth-order polynomials, which result in continuous-slope-of-curvature airfoils, with smooth Mach number and pressure distributions. This method is time consuming. The third method specifies the airfoil shapes by using a mixture of analytical polynomials and mapping the airfoil surfaces from a desirable curvature distribution. The third method provides blade surfaces with desirable performance in very few direct-design iterations. In all methods the geometry near the leading edge is specified by a thickness distribution added to a construction line, which eliminates the leading edge overspeed and laminar-separation regions. The blade-design methods presented in this paper can be used to improve the aerodynamic and heat transfer performance of turbomachinery cascades, and they can result in high-performance airfoils in very few iterations.

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8

Kidd, S. R., J. S. Barton, P. Meredith, J. D. C. Jones, M. A. Cherrett, and K. S. Chana. "A Fiber Optic Probe for Gas Total Temperature Measurement in Turbomachinery." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 635–41. http://dx.doi.org/10.1115/1.2836582.

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This paper describes the design, operation, construction, and demonstration of a new type of high-bandwidth unsteady temperature sensor based on fiber optics, and capable of operating in a high-speed multistage research compressor with flow representative of jet engine conditions. The sensing element is an optical coating of zinc selenide deposited on the end of an optical fiber. During evaluation in aerodynamic testing, a 1 K gas temperature resolution was demonstrated at 9.6 kHz and an upper bandwidth limit of 36 kHz achieved.

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9

Siddappaji, Kiran, and Mark G. Turner. "Versatile Tool for Parametric Smooth Turbomachinery Blades." Aerospace 9, no. 9 (August 31, 2022): 489. http://dx.doi.org/10.3390/aerospace9090489.

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Designing blades for efficient energy transfer by turning the flow and angular momentum change is both an art and iterative multidisciplinary engineering process. A robust parametric design tool with few inputs to create 3D blades for turbomachinery and rotating or non-rotating energy converters is described in this paper. The parameters include axial–radial coordinates of the leading/trailing edges, construction lines (streamlines), metal angles, thickness-to-chord ratio, standard, and user-defined airfoil type among others. Using these, 2D airfoils are created, conformally mapped to 3D stream surfaces, stacked radially with multiple options, and they are transformed to a 3D Cartesian coordinate system. Smooth changes in blade curvature are essential to ensure a smooth pressure distribution and attached flow. B-splines are used to control meanline curvature, thickness, leading edge shape, sweep-lean, and other parameters chordwise and spanwise, making the design iteration quick and easy. C2 curve continuity is achieved through parametric segments of cubic and quartic B-splines and is better than G2. New geometries using an efficient parametric scheme and minimal CAD interaction create watertight solid bodies and optional fluid domains. Several examples of ducted axial and radial turbomachinery with special airfoil shapes or otherwise, unducted rotors including propellers and wind and hydrokinetic turbines are presented to demonstrate versatility and robustness of the tool and can be easily tied to any automation chain and optimizer.

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Morgese, Gaetano, Francesco Fornarelli, Paolo Oresta, Tommaso Capurso, Michele Stefanizzi, Sergio M. Camporeale, and Marco Torresi. "Fast Design Procedure for Turboexpanders in Pressure Energy Recovery Applications." Energies 13, no. 14 (July 16, 2020): 3669. http://dx.doi.org/10.3390/en13143669.

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Sustainable development can no longer neglect the growth of those technologies that look at the recovery of any energy waste in industrial processes. For example, in almost every industrial plant it happens that pressure energy is wasted in throttling devices for pressure and flow control needs. Clearly, the recovery of this wasted energy can be considered as an opportunity to reach not only a higher plant energy efficiency, but also the reduction of the plant Operating Expenditures (OpEx). In recent years, it is getting common to replace throttling valves with turbine-based systems (tuboexpander) thus getting both the pressure control and the energy recovery, for instance, producing electricity. However, the wide range of possible operating conditions, technical requirements and design constrains determine highly customized constructions of these turboexpanders. Furthermore, manufacturers are interested in tools enabling them to rapidly get the design of their products. For these reasons, in this work we propose an optimization design procedure, which is able to rapidly come to the design of the turboexpander taking into account all the fluid dynamic and technical requirements, considering the already obtained achievements of the scientific community in terms of theory, experiments and numeric. In order to validate the proposed methodology, the case of a single stage axial impulse turbine is considered. However, the methodology extension to other turbomachines is straightforward. Specifically, the design requirements were expressed in terms of maximum allowable expansion ratio and flow coefficient, while achieving at least a minimum assigned value of the turbine loading factor. Actually, it is an iterative procedure, carried out up to convergence, made of the following steps: (i) the different loss coefficients in the turbine are set-up in order to estimate its main geometric parameters by means of a one dimensional (1D) study; (ii) the 2D blade profiles are designed by means of an optimization algorithm based on a “viscous/inviscid interaction” technique; (iii) 3D Computational Fluid Dynamic (CFD) simulations are then carried out and the loss coefficients are computed and updated. Regarding the CFD simulations, a preliminary model assessment has been performed against a reference case, chosen in the literature. The above-mentioned procedure is implemented in such a way to speed up the convergence, coupling analytical integral models of the 1D/2D approach with accurate local solutions of the finite-volume 3D approach. The method is shown to be able to achieve consistent results, allowing the determination of a turbine design respectful of the requirements more than doubling the minimum required loading factor.

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Barsi, Dario, Marina Ubaldi, Pietro Zunino, and Robert Fink. "Optimized Design of a Novel Hydraulic Propeller Turbine for Low Heads." Designs 5, no. 1 (March 12, 2021): 20. http://dx.doi.org/10.3390/designs5010020.

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In the present paper, an optimized design procedure capable of providing the geometry of a high efficiency compact hydraulic propeller turbine for low head is proposed and developed. The turbine preliminary design is based on fundamental turbomachinery mean-line equations and on the employment of statistical correlations, which relate the main geometrical parameters to the fundamental design parameters. The first obtained geometry represents the starting point of an automated aerodynamic single point optimization procedure based on a genetic algorithm generating and updating a wide database of turbine geometries. The approach employs a three-dimensional (3D) Reynolds averaged Navier–Stokes (RANS) solver for the construction of the corresponding database of performance. A meta-model, such as an artificial neural network (ANN), is used to speed up the design optimization process. The procedure has been applied on the practical case of a novel simplified hydraulic propeller turbine prototype for very low heads. The adopted design optimization procedure is able to modify the turbine blade and vane geometries in order to achieve automatically the targeted net head and the maximum for the total to total internal efficiency once diameter, mass flow rate, and rotational speed are assigned.

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Popova, Diana, Denis Popov, and Nikita Samoylenko. "INVESTIGATION OF THE GRID MODEL AND TURBULENCE MODEL PARAMETERS INFLUENCE ON QUALITY OF TURBINE ROTOR BLADE TIP CLEARANCE AREA AERODYNAMIC PROCESSES MODELING." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 66 (2021): 67–78. http://dx.doi.org/10.15593/2224-9982/2021.66.07.

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Aerodynamic processes mathematical modeling is carried out using numerical methods. Now the level of development of software numerical methods of three-dimensional gas-dynamic modeling of processes in turbomachinery makes it possible to determine with high accuracy the main characteristics of units at the design stage. It significantly reduces the time and cost of production. This article proposes a methodology for installation and improving the mathematical and grid model of HPT rotor blade to improve the quality of three-dimensional modeling. Aerodynamic processes mathematical modeling in aircraft turbojet engine blade rows is carried out using numerical methods. Grid model settings and turbulence model significantly affect the results qualitative characteristics and the calculations duration. This article proposes a methodology for grid model constructing based on local intense vortex formation and flow mixing places thickening. The influence of the grid and turbulence models parameters are estimated on the kinetic energy losses amount and secondary flows structure. The design model includes the building geometric model, preparation of the grid model and description of the turbulence model. Influence of grid and BSL and SST turbulence models on results of turbine blade aerodynamic calculation is considered in this article. Basic recommendations for the construction of mathematical and grid models in the ANSYS for uncooled rotor blades have been developed.

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Ainsworth, R. W., J. L. Allen, and J. J. M. Batt. "The Development of Fast Response Aerodynamic Probes for Flow Measurements in Turbomachinery." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 625–34. http://dx.doi.org/10.1115/1.2836581.

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The advent of a new generation of transient rotating turbine simulation facilities, where engine values of Reynolds and Mach number are matched simultaneously together with the relevant rotational parameters for dimensional similitude (Dunn et al., 1988; Epstein and Guenette, 1984; Ainsworth et al., 1988), has provided the stimulus for developing improved instrumentation for investigating the aerodynamic flows in these stages. Much useful work has been conducted in the past using hot-wire and laser anemometers. However, hot-wire anemometers are prone to breakage in the high-pressure flows required for correct Reynolds numbers. Furthermore, some laser techniques require a longer run-time than these transient facilities permit, and generally yield velocity information only, giving no data on loss production. Advances in semiconductor aerodynamic probes are beginning to fulfill this perceived need. This paper describes advances made in the design, construction, and testing of two and three-dimensional fast response aerodynamic probes, where semiconductor pressure sensors are mounted directly on the surface of the probes, using techniques that have previously been successfully used on the surface of rotor blades (Ainsworth et al., 1991). These are to be used to measure Mach number and flow direction in compressible unsteady flow regimes. In the first section, a brief review is made of the sensor and associated technology that has been developed to permit a flexible design of fast response aerodynamic probe. Following this, an extensive program of testing large-scale aerodynamic models of candidate geometries for suitable semiconductor scale probes is described, and the results of these discussed. The conclusions of these experiments, conducted for turbine representative mean and unsteady flows, yielded new information for optimizing the design of the small-scale semiconductor probes, in terms of probe geometry, sensor placement, and aerodynamic performance. Details are given of a range of wedge and pyramid semiconductor probes constructed, and the procedures used in calibrating and making measurements with them. Differences in performance are discussed, allowing the experimenter to choose an appropriate probe for the particular measurement required. Finally, the application of prototype semiconductor probes in a transient rotor experiment at HP turbine representative conditions is described, and the data so obtained are compared with CFD solutions of the unsteady viscous flow-field.

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Son, Seongmin, Yongju Jeong, Seong Kuk Cho, and Jeong Ik Lee. "Development of supercritical CO2 turbomachinery off-design model using 1D mean-line method and Deep Neural Network." Applied Energy 263 (April 2020): 114645. http://dx.doi.org/10.1016/j.apenergy.2020.114645.

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Wang, Yuqi, Qiuwan Du, Yunzhu Li, Di Zhang, and Yonghui Xie. "Field reconstruction and off-design performance prediction of turbomachinery in energy systems based on deep learning techniques." Energy 238 (January 2022): 121825. http://dx.doi.org/10.1016/j.energy.2021.121825.

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Du, Qiuwan, Like Yang, Liangliang Li, Tianyuan Liu, Di Zhang, and Yonghui Xie. "Aerodynamic design and optimization of blade end wall profile of turbomachinery based on series convolutional neural network." Energy 244 (April 2022): 122617. http://dx.doi.org/10.1016/j.energy.2021.122617.

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17

Yokota, Jeffrey W., and Adam J. Medd. "Convergence Acceleration of an Inverse Design Technique for Constructing Turbomachinery Cascades." AIAA Journal 38, no. 10 (October 2000): 1983–85. http://dx.doi.org/10.2514/2.854.

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Yokota, Jeffrey W., and Adam J. Medd. "Convergence acceleration of an inverse design technique for constructing turbomachinery cascades." AIAA Journal 38 (January 2000): 1983–85. http://dx.doi.org/10.2514/3.14637.

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Raheel, Muhammad M., and Abraham Engeda. "Systematic Design Approach for Radial Blade Regenerative Turbomachines." Journal of Propulsion and Power 21, no. 5 (September 2005): 884–92. http://dx.doi.org/10.2514/1.1426.

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Kim, Jun-Seong, You-Taek Kim, and Do-Yeop Kim. "Preliminary Design and Blade Optimization of a Two-Stage Radial Outflow Turbine for a CO2 Power Cycle." Energies 15, no. 17 (August 26, 2022): 6240. http://dx.doi.org/10.3390/en15176240.

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Recently, the CO2 power cycle has attracted attention because of tightening environmental regulations. The turbine is a factor that greatly affects the efficiency of the cycle. The radial outflow turbine is a turbomachine with the various advantages of an axial flow turbine and a radial inflow turbine, but the design theory for the turbine is uncertain. In this study, a preliminary design algorithm for a radial outflow turbine with a multi-stage configuration is presented. To verify the preliminary design algorithm, a preliminary design for a two-stage radial outflow turbine for a CO2 power cycle was carried out, and a computational fluid dynamic analysis was performed. Consequently, values close to the target performance were obtained, but blade optimization was performed to obtain more satisfactory results. The final geometry of the radial outflow turbine was obtained through optimization considering the blade exit angle related to the deviation angle, blade maximum thickness-true chord ratio, and incidence angle. In the final geometry, the error rates of power (W˙), efficiency (ηts), and pressure ratio (PRts) between target performance and computational fluid dynamic results were improved to 5.0%, 4.8%, and 1.8%, respectively. The performance and flow characteristics of the initial and final geometries were analyzed.

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Kovář, Patrik, Adam Tater, Pavel Mačák, and Tomáš Vampola. "Searching for the Most Suitable Loss Model Set for Subsonic Centrifugal Compressors Using an Improved Method for Off-Design Performance Prediction." Energies 14, no. 24 (December 18, 2021): 8545. http://dx.doi.org/10.3390/en14248545.

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This work investigates loss model sets based on empirical loss correlations for subsonic centrifugal compressors. These loss models in combination with off-design performance prediction algorithms make up an essential tool in predicting off-design behaviour of turbomachines. This is important since turbomachines rarely work under design conditions. This study employs an off-design performance prediction algorithm based on an iterative process from Galvas. Modelling of ten different loss mechanisms and physical phenomena is involved in this approach and is thoroughly described in this work. Geometries of two subsonic compressors were reconstructed and used in the evaluation of individual loss correlations in order to obtain a suitable loss model. Results of these variations are compared to experimental data. In addition, 4608 loss model sets were created by taking all possible combinations of individual loss estimations from which three promising candidates were selected for further investigation. Finally, off-design performance of both centrifugal compressors was computed. These results were compared to experimental data and to other loss model sets from literature. The newly composed loss model set No. 2137 approximates experimental data over a 21.2% better in relative error than the recent Zhang set and nearly a 36.7% better than the outdated Oh’s set. Therefore, set No. 2137 may contribute to higher precision of centrifugal turbomachines’ off-design predictions in the upcoming research.

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Shang, Peng, Ying Zhan, Sheng Feng, Jian Zhou, and Lie Yu. "Exact Solution of High-Speed Couplings for Interference Fits." Advanced Materials Research 744 (August 2013): 180–84. http://dx.doi.org/10.4028/www.scientific.net/amr.744.180.

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High-speed couplings are the key parts of micro-turbomachinerys. They are assembled to shafts by interference fits, which can transfer large torque, are easy to produce and offer significant cost advantages. Considering of the influences of the torque, rotational speed and temperature variation, the interference fits between couplings and shafts have to be analyzed accurately in order to save the construction cost and reducing risk of invalidation accidents. In this paper, a model of the interference fit between a coupling and a shaft is developed to study the determine parameters of the interference value. Using the classic elastic plane stress theory, the exact solutions of the radial stresses, hoop stresses and radial displacements are obtained. Three determine parameters (the torque, angular velocity and temperature variation correction terms) are derived in order to calculate the interference value. Taking a high-speed microturbomachinery for example, the numerical results show that the interference value is dependent of the ratios of inner radius to outer radius of the coupling and shaft significantly. The torque, angular velocity and temperature variation correction terms are in the same order of magnitude. The present analytical solutions are expected to be useful in the structure design of the interference fit between a high-speed coupling and a shaft.

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Bondar, V. S., D. A. Alkhimov, A. I. Fakeev, Y. M. Temis, D. A. Yakushev, and A. V. Pestov. "Computer-aided design of gas turbine engines rotors." Izvestiya MGTU MAMI 9, no. 1-4 (July 10, 2015): 10–20. http://dx.doi.org/10.17816/2074-0530-67096.

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The technology of the optimal design when designing the structure of the rotor disc for turbomachines is showed. The features of the organization of computer-aided design of gas turbine engine rotor are considered. The calculations of gas turbine engine rotor parts optimal form were made. Structural optimization (shape optimization) was applied to optimal design of compressor disk depending on various factors of loading and optimization criteria.

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Omidi, Mohammad, Shu-Jie Liu, Soheil Mohtaram, Hui-Tian Lu, and Hong-Chao Zhang. "Improving Centrifugal Compressor Performance by Optimizing the Design of Impellers Using Genetic Algorithm and Computational Fluid Dynamics Methods." Sustainability 11, no. 19 (September 30, 2019): 5409. http://dx.doi.org/10.3390/su11195409.

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It has always been important to study the development and improvement of the design of turbomachines, owing to the numerous uses of turbomachines and their high energy consumption. Accordingly, optimizing turbomachine performance is crucial for sustainable development. The design of impellers significantly affects the performance of centrifugal compressors. Numerous models and design methods proposed for this subject area, however, old and based on the 1D scheme. The present article developed a hybrid optimization model based on genetic algorithms (GA) and a 3D simulation of compressors to examine the certain parameters such as blade angle at leading and trailing edges and the starting point of splitter blades. New impeller design is proposed to optimize the base compressor. The contribution of this paper includes the automatic creation of generations for achieving the optimal design and designing splitter blades using a novel method. The present study concludes with presenting a new, more efficient, and stable design.

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Lu, Kun-Hsien, Hsiao-Wei D. Chiang, and Pei-Jen Wang. "Sensitivity Analysis of Transcritical CO2 Cycle Performance Regarding Isentropic Efficiencies of Turbomachinery for Low Temperature Heat Sources." Energies 15, no. 23 (November 24, 2022): 8868. http://dx.doi.org/10.3390/en15238868.

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The transcritical CO2 (T-CO2) power cycle using low temperature waste heat is a promising technique for energy saving and environmental protection. However, according to the literature, there is no commercialized unit in service yet. This study provides developers a reference to shorten the design phase of the T-CO2 cycle commercialization process. A sensitivity analysis of the system performance, i.e., thermal efficiency and net power output, regarding the isentropic efficiencies of pump (ηp) and expander (ηe) and the heat source temperature (Th,in) has been carried out using MATLAB and NIST REFPROP database. Simple and recuperative configurations are investigated based on their own optimal working pressures. The results show that the enhancement of ηe has a greater influence on improving the system performance, but the improvement will diminish as ηp, ηe, and Th,in increase. Although better system performance can be achieved with higher ηp, ηe, and Th,in, the cost of the system equipment will also increase due to the higher optimal working pressure. In addition, increasing ηp and ηe will negatively affect the effectiveness of the recuperator. Therefore, the turbomachinery efficiencies and the heat source temperature should be considered simultaneously for the most cost-effective system design.

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Papoutsis-Kiachagias, E. M., S. A. Kyriacou, and K. C. Giannakoglou. "The continuous adjoint method for the design of hydraulic turbomachines." Computer Methods in Applied Mechanics and Engineering 278 (August 2014): 621–39. http://dx.doi.org/10.1016/j.cma.2014.05.018.

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Dmitriev, V. T., D. R. Gabidullin, G. A. Boyarskikh, and A. O. Kochanov. "Choosing a construction of junction point of mining turbomachines and a collector." News of the Ural State Mining University, no. 1(45) (2017): 62–64. http://dx.doi.org/10.21440/2307-2091-2017-1-62-64.

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28

Epple, Ph, F. Durst, and A. Delgado. "A theoretical derivation of the Cordier diagram for turbomachines." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 225, no. 2 (July 19, 2010): 354–68. http://dx.doi.org/10.1243/09544062jmes2285.

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The design of high-efficiency fans is often based on the experience of the designer. In order to determine its main dimensions, fan designers use the Cordier diagram. For a given operating point (i.e. flowrate and pressure, and a rotating speed), the optimum diameter of high-efficiency fans can be found in the Cordier diagram. The Cordier diagram is an empirical diagram based on measurements. It delivers a relation between flowrate, pressure, rotating speed, and diameter. However, the Cordier diagram does not provide any information on the blade shape (i.e. the angles and the blade width). In order to fill this gap, there are design rules based on the experience of the designer and some analytical performance parameters in the literature. One very common performance parameter is the reaction, which is the ratio between the static and the total pressure rising from the impeller inlet to its outlet. These design rules and performance parameters are, however, of limited use. Therefore, the total-to-static ideal efficiency is introduced to yield, together with the speed and diameter numbers σ and δ, the essential parameters that distinguish the different turbomachines in the Cordier diagram. Based on the integral parameters of the flow and the geometry of turbomachines, a performance analysis of turbomachines is performed and the Cordier diagram is theoretically derived.

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29

Brighenti, Attilio, Davide Duranti, and Debora Quintabà. "TGSim Plus™—Real-Time Dynamic Simulation Suite of Gas Turbine Systems for the MATLAB®/Simulink® Environment." International Journal of Turbomachinery, Propulsion and Power 5, no. 3 (September 11, 2020): 24. http://dx.doi.org/10.3390/ijtpp5030024.

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Dynamic simulation of turbomachinery by Hardware in the Loop (HIL) real-time systems has become an essential practice, due to the high cost of real equipment testing and the need to verify the control and diagnostic systems’ reaction to emergency situations. The authors developed a full model of a power generation Gas Turbine Plant, including liquid and gaseous auxiliaries, and the electrical generator and starter motor, integrated in a MATLAB®/Simulink® simulation suite: TGSim Plus™. This allows assembling models of various gas turbine (GT) architectures by customised Simulink® library blocks and simulating steady state and transient conditions, such as complete start-up and shutdown operations as well as emergency, contingent operations and artificially injected fault scenarios. The model solver runs real-time steps at milliseconds scale. The paper describes the main modelling characteristics and typical results of steady state and transient simulations of a heavy-duty gas turbine under development by Doosan Heavy Industries and Construction (Changwon, South Korea). Comparison with benchmark design simulations obtained by a reference non real-time software shows a good match between the two environments, duly taking into account some differences in the GT models setting affecting parts of the sequence. The paper discusses also the bleed streams warm-up influence on GT performance and the start-up states trajectories dependency on control logic and on the starter helper motor torque envelope.

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Nikolaev, Vitaly S., Sergey A. Abalakin, and Igor V. Tishchenko. "Comparison of efficiency losses due to leaks for turbine units of aviation air conditioning systems with petal-type gas-dynamic bearings and ball bearings." Refrigeration Technology 111, no. 1 (September 7, 2022): 13–20. http://dx.doi.org/10.17816/rf96964.

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BACKGROUND: Designers of turbomachines strive to increase the efficiency of expanding compressed gases by reducing all kinds of energy losses, particularly due to clearances between the impeller and the body elements of the turbomachine. AIM: This article aimed to evaluate a possible increase in efficiency with a decrease in the radial and axial clearance between the blades of a radial-axial impeller and the casing of a centrifugal expander in the designs of turbomachines with ball bearings and petal-type gas-dynamic bearings. MATERIALS AND METHODS: The radial and axial clearances between the blades of the radial-axial impeller and the centrifugal expander casing in the designs of turbomachines with ball bearings and petal-type gas-dynamic bearings were compared by analyzing the experience of Russian and international experts in developing turbomachines. Models were presented for estimating the efficiency losses of a centrifugal expander depending on the value of the radial and axial clearances. A comparative calculation of the efficiency loss for medium- and high-cooling-capacity refrigeration turbines of aircraft air conditioning systems was performed. RESULTS: Based on the calculations, a conclusion was derived about the predominance of the influence of the radial clearance. The calculations revealed that with a decrease in the clearances between the impeller and the casing in a design with petal-type bearings, a refrigeration turbine of medium cooling capacity (16 kW, 2 impellers) can be expected to experience an increase in efficiency by an average of 2.3%; this expected increase is 0.75% to 1.4% for a high-capacity refrigeration turbine (55 kW, 3 or 4 impellers). Findings indicate that performing works to reduce radial clearances in the designs of turbomachines with petal-type gas-dynamic bearings is necessary.

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31

Makarov, Nikolai. "Mathematical model of jet control of adaptability of mine turbomachines." E3S Web of Conferences 177 (2020): 05008. http://dx.doi.org/10.1051/e3sconf/202017705008.

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Achieving synergies from high-tech industries in combination with environmental technologies of innovative subsurface use is possible only on the path to the formation of a qualitatively new approach to creation of energy-efficient technologies including assistive technologies. The lack of adaptability of turbomachines providing industrial safety by more than 15% increases the cost of production of mining and oil and gas complexes of the Russian Federation, reducing their competitiveness due to their low energy efficiency. An equation is derived in the article for calculating the circulation of a circular lattice of aero-gas-dynamic profiles as a function of the energy parameters of the sources and vortex chambers drains associated with the energy efficiency of turbomachines. The dominant influence of jet control over the flow profiles of impeller blades is proved due to the energy characteristics of sources and drains, which are associated with the parameters of the mine network. Improving the methodology for the aerodynamic calculation of circular lattice of aerodynamic profiles and the development of radial aerodynamic schemes with increased adaptability made it possible to derive an absolutely unique vector for the future development of fan construction, fundamentally based on nature-like technologies for energy conversion and transfer. The possibility of a significant increase in aerodynamic loading, adaptability and efficiency of mine turbomachines, made according to radial aerodynamic schemes with vortex chambers built into the blades of the impeller, which perform the functions of adaptive inkjet circulation control devices, is proved. According to the results of the research, the VRVP-8 radial-vortex fan was created, which has 55% greater energy efficiency in relation to fans of the VME VV type. Currently, turbomachines are being developed based on nature-like technologies in relation to the oil and gas industry.

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32

Rosa Taddei, S., and F. Larocca. "Axisymmetric design of axial turbomachines: An inverse method introducing profile losses." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 222, no. 6 (September 2008): 613–21. http://dx.doi.org/10.1243/09576509jpe644.

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33

Gundy-Burlet, K. L., M. M. Rai, R. C. Stauter, and R. P. Dring. "Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 2—Computational Assessment." Journal of Turbomachinery 113, no. 2 (April 1, 1991): 227–32. http://dx.doi.org/10.1115/1.2929090.

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Fluid dynamics of turbomachines are complicated because of aerodynamic interactions between rotors and stators. It is necessary to understand the aerodynamics associated with these interactions in order to design turbomachines that are both light and compact as well as reliable and efficient. The current study uses an unsteady, thin-layer Navier–Stokes zonal approach to investigate the unsteady aerodynamics of a multistage compressor. Relative motion between rotors and stators is made possible by the use of systems of patched and overlaid grids. Results have been computed for a 2 1/2-stage compressor configuration. The numerical data compare well with experimental data for surface pressures and wakes. In addition, the effect of grid refinement on the solution is studied.

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34

Tiainen, Jonna, Ahti Jaatinen-Värri, Aki Grönman, Petri Sallinen, Juha Honkatukia, and Toni Hartikainen. "Validation of the Axial Thrust Estimation Method for Radial Turbomachines." International Journal of Rotating Machinery 2021 (February 24, 2021): 1–18. http://dx.doi.org/10.1155/2021/6669193.

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The fast preliminary design and safe operation of turbomachines require a simple and accurate prediction of axial thrust. An underestimation of these forces may result in undersized bearings that can easily overload and suffer damage. While large safety margins are used in bearing design to avoid overloading, this leads to costly oversizing. In this study, the accuracy of currently available axial thrust estimation methods is analyzed by comparing them to each other and to theoretical pressure distribution, numerical simulations, and new experimental data. Available methods tend to underestimate the maximum axial thrust and require data that are unavailable during the preliminary design of turbomachines. This paper presents a new, simple axial thrust estimation method that requires only a few preliminary design parameters as the input data and combines the advantages of previously published methods, resulting in a more accurate axial thrust estimation. The method is validated against previously public data from a radial pump and new experimental data from a centrifugal compressor, the latter measured at Lappeenranta-Lahti University of Technology LUT, Finland, and two gas turbines measured at Aurelia Turbines Oy, Finland. The maximum deviation between the estimated axial thrust using the hybrid method and the measured one is less than 13%, while the other methods deviate by tens of percent.

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35

MAKAROV, Nikolay, Vladimir MAKAROV, Aleksandr UGOLNIKOV, and Mikhail NOSYREV. "OPTIMIZATION OF PARAMETERS OF FAN UNITS OF AIR COOLING DEVICES." Sustainable Development of Mountain Territories 13, no. 3 (September 30, 2021): 433–40. http://dx.doi.org/10.21177/1998-4502-2021-13-3-433-440.

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Purpose of the study. Optimization of the parameters of high speed fan units of air coolers, the combination of which achieves the highest economic efficiency of fan units and, accordingly, the most rational range of specific speed values for the modes of maximum efficiency of fan units in combination with the relative diameter of the sleeve. Development of a mathematical model for determining the local values of the parameters of the efficiency of highspeed fan installations. Sustainable development of territories with active subsoil use is closely related to solving the problems of improving industrial safety and the efficiency of cooling the compressed gas at compressor stations of main gas pipelines, which actualizes the problem of mathematical modeling of energy conversion processes in the impellers of fan units of gas air coolers (AVO) to increase the competitiveness of the oil and gas complex RF in the context of globalization. Research methods. To optimize and determine the limiting combination of calculated parameters, the mathematical method of searching for the area of local maxima of a multiparameter problem in this part was performed in two stages: a mathematical model was built for determining the local values of the parameters that ensure the highest efficiency of fan installations with high speed; the most rational limiting combination of design parameters was determined, at which the highest economic efficiency of fan installations is achieved. Research results. The possibility of increasing the economic efficiency of axial fan units of high speed, made according to aerodynamic schemes with one impeller for gas air cooling devices, has been established. Using the mathematical analysis of the basic laws of axial turbomachines, equations for the efficiency of a fan unit and a fan are obtained, depending on the specific speed. Formulas are obtained for the maximum values of the efficiency of the fan and the fan unit of various specific speed depending on the coefficient of the consumpconsumption speed and on the relative diameter of the impeller sleeve. A method is proposed for constructing aerodynamic schemes of axial fan units for air-cooled gas coolers of the "K" type with maximum maximum values of efficiency for given values of specific speed, relative diameter of the impeller sleeve, aerodynamic quality of the impeller profiles, coefficient of aerodynamic resistance of the flow path of the coefficient of flow velocity. The possibility of creating a fan installation with a speed of ny ≥ 400 with an efficiency of at least ηy=0,86. Application area. Enterprises of the oil and gas complex of the Russian Federation for cooling compressed gas using AVO compressor stations of main gas pipelines.

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36

Humm, H. J., C. R. Gossweiler, and G. Gyarmathy. "On Fast-Response Probes: Part 2—Aerodynamic Probe Design Studies." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 618–24. http://dx.doi.org/10.1115/1.2836580.

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The influence of the probe size and geometry on the quality of fast-response measurements in turbomachines has been experimentally investigated. For investigations in the static domain (time-independent flows) probes were calibrated in two continuously operating wind tunnels in the range 0.2 < M < 1.2. For dynamic calibrations in time-variant flows model experiments in water (0.025 < k < 0.4, reduced frequency) were performed. Aerodynamic characteristics were determined for a great number of probe geometries, such as circular cylinders and wedge-type probes with varied apex angles, locations of the sensing holes, and leading edge shapes. The experiments comprised investigations in tolerance ranges for prismatic total pressure probes, yaw angle sensitivity, yaw angle, and Mach number effects on calibration and influence of dynamic yaw angle fluctuation on probe characteristics. As a result of the experiments errors due to static and dynamic aerodynamic effects could be quantified. The majority of the errors arising during measurements in turbomachines can be directly related to the probe size. An important number of these errors are systematic and can be analytically modeled and hence their influence corrected. In fluctuating flows the most severe measurement errors, which often may exceed the quantity of interest, are due to dynamic stall effects. This phenomenon, which is of transient nature and cannot be corrected, is typical for sharp wedge probes, but is not present with circular cylinders, and the effects are much smaller with very blunt wedges.

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37

Repetckii, Oleg, and Van Vinh Nguyen. "DYNAMIC CHARACTERISTICS ANALYSIS OF BLADED DISK TURBOMACHINES BASED ON INTENTIONAL MISTUNING." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 61–70. http://dx.doi.org/10.15593/2224-9982/2020.62.07.

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To increase technical level of energy turbomachine in modern turbomachinery, high reliability and durability of structures are required in the design, manufacture and operation of turbomachine. Any change geometry, mass, material properties of the bladed disk of turbomachine in the design is called mistuning parameters. With a small value of mistuning blades can significantly increase amplitude, displacement or stresses of the blades structures. So, analysis influence of the effect mistuning parameters on the dynamic characteristics in the field of turbomachine is an important and urgent task. This article analyzes the effect intentional mistuning of the axial bladed disk turbomachine in order to reduce forced response due to low-order engine excitation. The maximum value forced response of rotor blades turbomachine with mistuning parameters is usually much more than that of the tuned rotors. An increase level mistuning of this critical value actually leads to a decrease magnifications of the forced response. Thus, the actual work has been introducing some degree of intentional mistuning in the design to achieve these purposes. In this paper, we study the effectiveness of intentional mistuning at the design stage bladed disk turbomachine, which is introduced into the rotor design by changing the nominal mass of the blades in harmonic Формаls.

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38

Yoo, I. S., M. R. Park, and M. K. Chung. "Improved momentum exchange theory for incompressible regenerative turbomachines." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 7 (November 1, 2005): 567–81. http://dx.doi.org/10.1243/095765005x31252.

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On the basis of the momentum exchange theory, an improved mathematical model is developed to analyse the complicated helical flow in regenerative turbomachines and to suggest a systematic way to design such kind of machines. The helical flow in the machines is resolved into a peripheral component and a circulatory component, and a theoretically sound method is proposed to calculate the circulatory flow velocity and slip factor, which are closely related to the machine performance. To implement the present method, the concepts of a circulatory pivot and an effectiveness of the circulatory flow are introduced. The circulatory flow loss was successfully estimated by introducing a bend-combination factor by adding four right angle bends losses. It was found that the overall head rise and the hydraulic efficiency can be accurately predicted by the proposed model equation and the present loss models. Development of the static pressure along the peripheral direction could be predicted satisfactorily.

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39

Mostefa, Brihmat, Refassi Kaddour, Douroum Embarek, and Kouadri Amar. "Analysis and Optimization of the Performances of the Centrifugal Compressor Using the CFD." International Journal of Heat and Technology 39, no. 1 (February 28, 2021): 107–20. http://dx.doi.org/10.18280/ijht.390111.

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Centrifugal compressors have been used in many areas of the machinery. The centrifugal compressor design is very complex, and a unique design system needs to be developed. A centrifugal compressor design system should be easy to use in interface and also flexible for inputs and outputs. The design tool also needs to be able to predicate the compressor performance in a fairly accurate level. In this study, we have developed a general analyses and optimization approach in the design and performance analysis of centrifugal turbomachines. This approach is based on different methods starting from a 1D approach up to the 3D study of the internal flow. It presents itself as a robust procedure for predicting and understanding the phenomena associated with the operation of turbomachines, but also for predicting performance. Current design system includes initial parameter studies, throughflow calculation, impeller design. The main improvements of the design system are adding the interface to allow users easy to use, adding the input and output capabilities and modifying few correlations. Current design system can predict the blade loading and compressor performance better compared with original design system. To check the aerodynamic appearance of the centrifugal compressor impeller blades, we must change the impeller dimensions and focus on changing axial length, but when changing the blade numbers, the model that improved efficiency and power at the same time introduced a design with a 0.274% and 10.735% improvement in each respectively in comparison to the initial impeller at the design point.

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40

Nava, P., N. Paone, G. L. Rossi, and E. P. Tomasini. "Design and Experimental Characterization of a Nonintrusive Measurement System of Rotating Blade Vibration." Journal of Engineering for Gas Turbines and Power 116, no. 3 (July 1, 1994): 657–62. http://dx.doi.org/10.1115/1.2906870.

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A measurement system for nonintrusive monitoring of rotating blade vibration in turbomachines based on fiber optic sensors is presented. The design of the whole system is discussed; the development of special purpose sensors, their interfacing to the data acquisition system, and the signal processing are outlined. The processing algorithms are tested by software simulation for several possible blade vibrations. Experimental tests performed on different bladed rotors are presented. Results are compared to simultaneous strain gage measurements.

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41

Xu, Kunbo, Yun Shi, Weiyang Qiao, and Zhirong Wang. "The Methodological and Experimental Research on the Identification and Localization of Turbomachinery Rotating Sound Source." Energies 15, no. 22 (November 17, 2022): 8647. http://dx.doi.org/10.3390/en15228647.

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The localization and quantification of turbomachinery rotating sound sources is an important challenge in the field of aeroacoustics. In order to compensate the motion of a rotating sound source, a rotating beamforming technique is developed and applied in a flow duct, which uses a wall-mounted microphone array placed circularly parallel to the fan, to detect the broadband noise source of the aeroengine fan. A simulation of three discrete rotating sound sources with a non-constant rotational speed is pursued to verify the effectiveness in reconstruction of the correct source positions and quantitative prediction of the source amplitudes. The technique is ulteriorly experimentally implemented at an axial low-speed fan test rig facility. The fan test rig has 19 rotor blades and 18 stator vanes, with a design speed up to 3000 rpm. The method can accurately identify the radial and circumferential positions of the three rotating sound sources in the simulation case, large side-lobes appear near the main-lobe of the sound source due to the geometric influence of the microphone array. A noticeable feature of beamforming images for axial flow fan is that the sound sources appear to be concentrated in the tip region rather than distributed along the span.

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42

Herr, Christiane M. "Design Is Construction, Construction Is Design." She Ji: The Journal of Design, Economics, and Innovation 5, no. 4 (2019): 367–69. http://dx.doi.org/10.1016/j.sheji.2019.11.007.

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43

Zhang, Mingjie, Jiangang Yang, Wanfu Zhang, and Qianlei Gu. "Tortuous flow path design for leakage reduction of labyrinth seal." Journal of Physics: Conference Series 2336, no. 1 (August 1, 2022): 012007. http://dx.doi.org/10.1088/1742-6596/2336/1/012007.

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Abstract This study proposes a new seal design to reduce the leakage in turbomachines. On the basis of the conventional labyrinth seal, two vertical blocking walls are added on the rotor, and one horizontal blocking wall is added on the upstream seal tooth and downstream seal tooth. In the new seal, a tortuous flow path is generated, and many vortexes appear. The new seal increases the resistance to the leakage fluid and kinetic energy dissipation. After the comparison of the leakage between the specially designed new seal and conventional labyrinth seal, it can be found that the specially designed new seal yields a reduction in the leakage of 42.7~43.6%.

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44

VANEEV, SERGEJ, VASYL MARTSYNKOVSKYY, MICHAL HATALA, DMYTRO MIROSHNICHENKO, YAROSLAV BILYK, DMYTRO SMOLENKO, ANDREY LAZARENKO, and FRANTISEK BOTKO. "RESULTS OF THE STUDY OF A TURBOGENERATOR WITH A PERIPHERAL-SIDE CHANNEL IN NON-DIMENSIONAL AND CRITERIAL COMPLEXES." MM Science Journal 2022, no. 3 (September 27, 2022): 5913–17. http://dx.doi.org/10.17973/mmsj.2022_10_2022008.

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Dimensionless and criterial complexes are successfully used in many technical fields. They play an important role in research and design. There are a large number of dimensionless and criterial complexes, which have their advantages and are chosen depending on the topic and specific objectives of the study. The article considers dimensionless and criterial complexes most often used in studies of turbomachines, in particular vortex expansion machines - relative internal (isoentropic) efficiency, degree of pressure drop, adjusted wheel speed, speed coefficient, adjusted diameter, flow factor and coefficient. The authors processed the data of the experimental study of the turbogenerator with a peripheral-side channel and presented them in the form of graphical dependences using these complexes. The improvement of these energy-saving turbogenerators is important because they are used to generate electricity from excess gas pressure, are considered environmentally friendly and are needed for the development of distributed energy. Vortex expansion machines with a peripheral-lateral channel are also poorly understood, so the topic is relevant. In this study, their area of use was determined and reflected in the ns - Ds diagram among radial and other vortex expansion turbomachines to facilitate their comparison and design.

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45

Piekos, E. S., and K. S. Breuer. "Pseudospectral Orbit Simulation of Nonideal Gas-Lubricated Journal Bearings for Microfabricated Turbomachines." Journal of Tribology 121, no. 3 (July 1, 1999): 604–9. http://dx.doi.org/10.1115/1.2834110.

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A journal bearing simulation tool developed to aid the design of the MIT microturbo-machine bearings is described. This tool uses an orbit method with a pseudospectral technique for treating the Reynolds equation. Comparison is made to various published data. Two types of stability chart are presented and their application to turbo-machine bearing design is discussed. Simulations of imbalance, noncircular geometry, and nonuniform pressures at the bearing ends are also demonstrated.

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46

Campi, Federico, Marco Mandolini, Federica Santucci, Claudio Favi, and Michele Germani. "PARAMETRIC COST MODELLING OF COMPONENTS FOR TURBOMACHINES: PRELIMINARY STUDY." Proceedings of the Design Society 1 (July 27, 2021): 2379–88. http://dx.doi.org/10.1017/pds.2021.499.

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AbstractThe ever-increasing competitiveness, due to the market globalisation, has forced the industries to modify their design and production strategies. Hence, it is crucial to estimate and optimise costs as early as possible since any following changes will negatively impact the redesign effort and lead time.This paper aims to compare different parametric cost estimation methods that can be used for analysing mechanical components. The current work presents a cost estimation methodology which uses non-historical data for the database population. The database is settled using should cost data obtained from analytical cost models implemented in a cost estimation software. Then, the paper compares different parametric cost modelling techniques (artificial neural networks, deep learning, random forest and linear regression) to define the best one for industrial components.Such methods have been tested on 9 axial compressor discs, different in dimensions. Then, by considering other materials and batch sizes, it was possible to reach a training dataset of 90 records. From the analysis carried out in this work, it is possible to conclude that the machine learning techniques are a valid alternative to the traditional linear regression ones.

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47

González, José, Laura Delgado, Sandra Velarde-Suárez, Jesús M. Fernández-Oro, Katia Mª Argüelles Díaz, David Rodríguez, and David Méndez. "Experimental study of the unsteady vibration signature for a Sirocco fan unit." Journal of Low Frequency Noise, Vibration and Active Control 39, no. 1 (April 7, 2019): 129–48. http://dx.doi.org/10.1177/1461348419837418.

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The small forward-curved blades known as Sirocco fan units are very common and widespread solution for air conditioning used in public transportation applications, as buses or trains. The users quietness and comfort have become a main concerns in the automotive industry. For such kind of turbomachinery flow , the patterns becomes always highly 3D and unsteady, compromising the referred comfort, and setting the focus on the working flow variables. A mathematically exact solution for that flow, which would provide any required information on pressure or forces, is out of scope at the current engineering design processes. Nevertheless, some flow features and mechanical data are needed to progress in the frame of a modern industrial environment, involving maintenance protocols with important temporal and economic constraints for different design procedures. The correctness of a given maintenance protocol relies on its feasibility to handle a set of machine working parameters or variables, including a number of them as wide as possible. Doing so, a set of not-dangerous ranges for them can be established. Such ranges are often defined promoting a series of failures similar to real ones, when the machine is in its operative lifetime. In this paper and in order to establish proper working ranges for maintenance purposes, a series of failures have been experimentally tested for a Sirocco fan unit. Initially, real data from industry have been required and a list of main failures was made, including (1) impeller or rotor unbalance, (2) impeller channel obstruction and (3) blocked inlet. The failures are studied using a purified orbit diagram (POD) technique and a symmetrized dot pattern (SDP) technique. All four working conditions are studied for at least three different flow rates and, therefore, a deeper insight into the fan working parameters and options are made feasible. In the frame of the maintenance protocol, a full set of ranges for the considered failures has been obtained. Therefore, the present paper shows a novel possibility to enhance existing maintenance protocol using two advanced frequency-based techniques.

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Siddique, M. Hamid, Arshad Afzal, and Abdus Samad. "Design Optimization of the Centrifugal Pumps via Low Fidelity Models." Mathematical Problems in Engineering 2018 (June 21, 2018): 1–14. http://dx.doi.org/10.1155/2018/3987594.

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Low fidelity model assisted design optimization of turbomachines has reduced the total computational and experimental costs. These models are called surrogate models which mimic the actual experiments or simulations. The surrogate models can generate thousands of approximate results from a few samples, making it easy to locate the optimal solution. Ample articles reported surrogate assisted design optimization of centrifugal pumps. In this article, the authors try to give a brief overview of the surrogate based optimization technique along with its historical applications and trend of the recent use. The various key design parameters which affect the performance of the centrifugal pump have also been discussed. The effectiveness of the surrogate based optimization technique and corresponding performance metrics have been discussed.

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Hasmatuchi, Vlad, Alin Bosioc, Sébastien Luisier, and Cécile Münch-Alligné. "A Dynamic Approach for Faster Performance Measurements on Hydraulic Turbomachinery Model Testing." Applied Sciences 8, no. 9 (August 21, 2018): 1426. http://dx.doi.org/10.3390/app8091426.

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During the design and optimization of hydraulic turbomachines, the experimental evaluation of hydraulic performances beyond the best efficiency point and for off-design conditions remains essential to validate the simulation process and to finalize the development. In this context, an alternative faster method to measure the efficiency of hydraulic turbomachines using a dynamic approach has been investigated. The so-called “sliding-gate” dynamic measurement method has been adapted and implemented on the hydraulic test rig of the HES-SO Valais//Wallis, Sion, Switzerland. This alternative approach, particularly gainful for small-hydro for which the investment devoted to development is limited, has been successfully assessed on two cases for drinking water networks energy recovery. A 2.65 kW double-regulated laboratory prototype of a tubular axial micro-turbine with two independent variable speed counter-rotating runners and a 11 kW multi-stage centrifugal pump-as-turbine (PAT) with variable speed have been selected. The hydraulic efficiency results obtained by dynamic measurements are compared to the ones obtained by the classical steady point-by-point method. This dynamic method, suitable not only for hydraulic machinery, allows: (i) reducing significantly (up to 10×) the time necessary to draw the complete efficiency characteristics of a hydraulic machine; (ii) rapidly detecting the hydrodynamic instabilities within the operating range of the machine.

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Asuaje, M., F. Bakir, S. Kouidri, R. Noguera, and R. Rey. "Computer-aided design and optimization of centrifugal pumps." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 3 (May 1, 2005): 187–93. http://dx.doi.org/10.1243/095765005x7556.

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Improvement in computer power and the development of numerical computational methods over the last few years have allowed the emergence of computational fluid dynamic (CFD) codes, making possible the numerical simulation of flow and energy transfer in turbomachines. To improve the efficiency of these tools, fast design software must be used. Within the framework of the optimization process of centrifugal pumps, HELIOX software was developed. It is a tool for design and performance analysis of centrifugal pumps. HELIOX allows quick design of new pumps and improvement of existing ones. HELIOX's performance analysis has been validated through many industrial cases: approximately 100 machines of different sizes and mechanical power. Heliox can be linked to quasi-and three-dimensional analysis tools; these tools enable a better understanding of physical phenomena so as to control the flow fields inside pumps.

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