Relevant bibliographies by topics / Radial Turbomachinery design

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  2. Dissertations / Theses
  3. Books
  4. Book chapters
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Academic literature on the topic 'Radial Turbomachinery design'

Author: Grafiati
Published: 6 September 2023

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Journal articles on the topic "Radial Turbomachinery design"

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Schröder, Tilman Raphael, Hans-Josef Dohmen, Dieter Brillert, and Friedrich-Karl Benra. "Impact of Leakage Inlet Swirl Angle in a Rotor–Stator Cavity on Flow Pattern, Radial Pressure Distribution and Frictional Torque in a Wide Circumferential Reynolds Number Range." International Journal of Turbomachinery, Propulsion and Power 5, no. 2 (April 17, 2020): 7. http://dx.doi.org/10.3390/ijtpp5020007.

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In the side-chambers of radial turbomachinery, which are rotor–stator cavities, complex flow patterns develop that contribute substantially to axial thrust on the shaft and frictional torque on the rotor. Moreover, leakage flow through the side-chambers may occur in both centripetal and centrifugal directions which significantly influences rotor–stator cavity flow and has to be carefully taken into account in the design process: precise correlations quantifying the effects of rotor–stator cavity flow are needed to design reliable, highly efficient turbomachines. This paper presents an experimental investigation of centripetal leakage flow with and without pre-swirl in rotor–stator cavities through combining the experimental results of two test rigs: a hydraulic test rig covering the Reynolds number range of 4 × 10 5 ≤ R e ≤ 3 × 10 6 and a test rig for gaseous rotor–stator cavity flow operating at 2 × 10 7 ≤ R e ≤ 2 × 10 8 . This covers the operating ranges of hydraulic and thermal turbomachinery. In rotor–stator cavities, the Reynolds number R e is defined as R e = Ω b 2 ν with angular rotor velocity Ω , rotor outer radius b and kinematic viscosity ν . The influence of circumferential Reynolds number, axial gap width and centripetal through-flow on the radial pressure distribution, axial thrust and frictional torque is presented, with the through-flow being characterised by its mass flow rate and swirl angle at the inlet. The results present a comprehensive insight into the flow in rotor–stator cavities with superposed centripetal through-flow and provide an extended database to aid the turbomachinery design process.
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Denton, J. D., and L. Xu. "The exploitation of three-dimensional flow in turbomachinery design." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 213, no. 2 (February 1, 1998): 125–37. http://dx.doi.org/10.1243/0954406991522220.

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Many of the phenomena involved in turbomachinery flow can be understood and predicted on a two-dimensional (2D) or quasi-three-dimensional (Q3D) basis, but some aspects of the flow must be considered as fully three-dimensional (3D) and cannot be understood or predicted by the Q3D approach. Probably the best known of these fully 3D effects is secondary flow, which can only be predicted by a fully 3D calculation which includes the vorticity at inlet to the blade row. It has long been recognized that blade sweep and lean also produce fully 3D effects and approximate methods of calculating these have been developed. However, the advent of fully 3D flow field calculation methods has made predictions of these complex effects much more readily available and accurate so that they are now being exploited in design. This paper will attempt to describe and discuss fully 3D flow effects with particular reference to their use to improve turbomachine performance. Although the discussion is restricted to axial flow machines, many of the phenomena discussed are equally applicable to mixed and radial flow turbines and compressors.
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Перевезенцев, Виктор, Viktor Perevezentsev, Максим Шилин, and Maksim Shilin. "Improving the design of the seal gaps in the flow of the pumping unit GTK-10-4." Bulletin of Bryansk state technical university 2015, no. 1 (March 31, 2015): 35–40. http://dx.doi.org/10.12737/22746.

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Describes the methods of modernization seal the radial clearance of the gas turbine by using the honeycomb structure at the periphery of the wheel. Discusses the gas-dynamic and thermal engineering problems using honeycomb seals in turbomachinery.
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Fei, Cheng-Wei, Wen-Zhong Tang, Guang-chen Bai, and Zhi-Ying Chen. "A dynamic probabilistic design method for blade-tip radial running clearance of aeroengine high-pressure turbine." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 229, no. 10 (August 28, 2014): 1861–72. http://dx.doi.org/10.1177/0954406214549267.

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Around the engineering background of the probabilistic design of high-pressure turbine (HPT) blade-tip radial running clearance (BTRRC) which conduces to the high-performance and high-reliability of aeroengine, a distributed collaborative extremum response surface method (DCERSM) was proposed for the dynamic probabilistic analysis of turbomachinery. On the basis of investigating extremum response surface method (ERSM), the mathematical model of DCERSM was established. The DCERSM was applied to the dynamic probabilistic analysis of BTRRC. The results show that the blade-tip radial static clearance δ = 1.82 mm is advisable synthetically considering the reliability and efficiency of gas turbine. As revealed by the comparison of three methods (DCERSM, ERSM, and Monte Carlo method), the DCERSM reshapes the possibility of the probabilistic analysis for turbomachinery and improves the computational efficiency while preserving computational accuracy. The DCERSM offers a useful insight for BTRRC dynamic probabilistic analysis and optimization. The present study enrichs mechanical reliability analysis and design theory.
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Jahn, Ingo, and Peter Jacobs. "Using Meridional Streamline and Passage Shapes to Generate Radial Turbomachinery Geometry and Meshes." Applied Mechanics and Materials 846 (July 2016): 1–6. http://dx.doi.org/10.4028/www.scientific.net/amm.846.1.

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An important aspect for structural and aerodynamics design of radial flow turbomachinery is the definition of the geometry and the generation of meshes for computational analysis. Particularly in the area of computational design and optimization, the way the geometry is defined is important, as it can limit design space. Traditionally, radial compressors and radial turbine rotors are defined using a mechanical design approach. Effectively a hub and shroud profile, followed by a rotorblade geometry are defined and the shape is adjusted in order to meet certain aerodynamic boundary conditions. The current paper presents an alternative approach, in which the overall geometry is defined starting from an aerodynamic requirement. The corresponding rotor and blade geometry is generated automatically, based on certain constraints. The advantage of this approach is the ability to define directly the aerodynamic requirements, which may allow a simpler efficient optimization of the aerodynamics.
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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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Kirk, R. G. "Evaluation of AMB Turbomachinery Auxiliary Bearings." Journal of Vibration and Acoustics 121, no. 2 (April 1, 1999): 156–61. http://dx.doi.org/10.1115/1.2893958.

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The use of active magnetic bearings (AMB) for turbomachinery has experienced substantial growth during the past two decades. The advantages for many applications make AMB’s a very attractive solution for potentially low loss and efficient support for both radial and thrust loads. New machinery must be shop tested prior to shipment to the field for installation on-line. For AMB turbomachinery, one additional test is the operation of the auxiliary drop or overload bearings. A major concern is ability of the selected auxiliary bearing to withstand the contact forces following an at speed rotor drop. The proper design of AMB machinery requires the calculation of the anticipated loading for the auxiliary bearings. Analytical techniques to predict the rotor transient response are reviewed. Results of transient response evaluation of a full-size compressor rotor are presented to illustrate some of the important parameters in the design for rotor drop.
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Schröder, Tilman, Sebastian Schuster, and Dieter Brillert. "Experimental Investigation of Centrifugal Flow in Rotor–Stator Cavities at High Reynolds Numbers >108." International Journal of Turbomachinery, Propulsion and Power 6, no. 2 (May 26, 2021): 13. http://dx.doi.org/10.3390/ijtpp6020013.

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The designers of radial turbomachinery need detailed information on the impact of the side chamber flow on axial thrust and torque. A previous paper investigated centripetal flow through narrow rotor–stator cavities and compared axial thrust, rotor torque and radial pressure distribution to the case without through-flow. Consequently, this paper extends the investigated range to centrifugal through-flow as it may occur in the hub side chamber of radial turbomachinery. The chosen operating conditions are representative of high-pressure centrifugal compressors used in, for example, carbon capture and storage applications as well as hydrogen compression. To date, only the Reynolds number range up to Re=2·107 has been investigated for centrifugal through-flow. This paper extends the range to Reynolds numbers of Re=2·108 and reports results of experimental and numerical investigations. It focuses on the radial pressure distribution in the rotor–stator cavity and shows the influence of the Reynolds number, cavity width and centrifugal mass flow rate. It therefore extends the range of available valid data that can be used to design radial turbomachinery. Additionally, this analysis compares the results to data and models from scientific literature, showing that in the higher Reynolds number range, a new correlation is required. Finally, the analysis of velocity profiles and wall shear delineates the switch from purely radial outflow in the cavity to outflow on the rotor and inflow on the stator at high Reynolds numbers in comparison to the results reported by others for Reynolds numbers up to Re=2·107.
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Salah, Salma I., Mahmoud A. Khader, Martin T. White, and Abdulnaser I. Sayma. "Mean-Line Design of a Supercritical CO2 Micro Axial Turbine." Applied Sciences 10, no. 15 (July 23, 2020): 5069. http://dx.doi.org/10.3390/app10155069.

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Supercritical carbon dioxide (sCO2) power cycles are promising candidates for concentrated-solar power and waste-heat recovery applications, having advantages of compact turbomachinery and high cycle efficiencies at heat-source temperature in the range of 400 to 800 ∘C. However, for distributed-scale systems (0.1–1.0 MW) the choice of turbomachinery type is unclear. Radial turbines are known to be an effective machine for micro-scale applications. Alternatively, feasible single-stage axial turbine designs could be achieved allowing for better heat transfer control and improved bearing life. Thus, the aim of this study is to investigate the design of a single-stage 100 kW sCO2 axial turbine through the identification of optimal turbine design parameters from both mechanical and aerodynamic performance perspectives. For this purpose, a preliminary design tool has been developed and refined by accounting for passage losses using loss models that are widely used for the design of turbomachinery operating with fluids such as air or steam. The designs were assessed for a turbine that runs at inlet conditions of 923 K, 170 bar, expansion ratio of 3 and shaft speeds of 150k, 200k and 250k RPM respectively. It was found that feasible single-stage designs could be achieved if the turbine is designed with a high loading coefficient and low flow coefficient. Moreover, a turbine with the lowest degree of reaction, over a specified range from 0 to 0.5, was found to achieve the highest efficiency and highest inlet rotor angles.
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Yang, Y. L., C. S. Tan, and W. R. Hawthorne. "Aerodynamic Design of Turbomachinery Blading in Three-Dimensional Flow: An Application to Radial Inflow Turbines." Journal of Turbomachinery 115, no. 3 (July 1, 1993): 602–13. http://dx.doi.org/10.1115/1.2929297.

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A computational method based on a theory for turbomachinery blading design in three-dimensional inviscid flow is applied to a parametric design study of a radial inflow turbine wheel. As the method requires the specification of swirl distribution, a technique for its smooth generation within the blade region is proposed. Excellent agreements have been obtained between the computed results from this design method and those from direct Euler computations, demonstrating the correspondence and consistency between the two. The computed results indicate the sensitivity of the pressure distribution to a lean in the stacking axis and a minor alteration in the hub/shroud profiles. Analysis based on a Navier–Stokes solver shows no breakdown of flow within the designed blade passage and agreement with that from a design calculation; thus the flow in the designed turbine rotor closely approximates that of an inviscid one. These calculations illustrate the use of a design method coupled to an analysis tool for establishing guidelines and criteria for designing turbomachinery blading.
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Dissertations / Theses on the topic "Radial Turbomachinery design"

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Albusaidi, Waleed. "Techno-economic assessment of radial turbomachinery in process gas applications." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9872.

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This research aims to assess the causes of inefficient and unstable operation of centrifugal compressors and turboexpanders in process gas applications in order to provide a solution for performance restoration and enhancement. It encompasses thermodynamic and flow evaluations to examine the efficiency and operating range improvement options of new units. Besides, this work is complemented by a technoeconomic analysis to provide a rounded outcome from these studies. In order to achieve the desired objectives, a novel integrated approach has been developed to assess the design and performance of multi-stage centrifugal compressors. The proposed systematic methodology involves five basic elements including evaluation of compressor selection, compressor sizing and casing structure, performance prediction at the design and off-design conditions, modelling of efficiency and head deterioration causes; and stage design evaluation. This will contribute towards evaluating the geometrical parameters of the new units’ designs at the early preliminary design phase, and thus, will be useful to identify the options for efficiency and operating range enhancements. For installed units, this approach can be implemented to assess the cause of inefficient and unstable operation by assessing the available operation data. A method was developed to predict the performance curve of multi-stage centrifugal compressor based on a stage stacking technique. This approach considers the advantages of Lüdtke and Casey-Robinson methods with an incorporation of a methodology for compressor selection and sizing to generate more accurate results. To emphasize the validity of the developed model, it has been evaluated for both low and high flow coefficient applications. The obtained results show a significant improvement in the estimated efficiency, pressure ratio, shaft power and operating range as compared with the existing methods. The centrifugal compressor is designed to run under various operating conditions and different gas compositions with the primary objective of high efficiency and reliability. Therefore, a new iterative method has been developed to predict the equivalent compressor performance at off-design conditions. This technique uses the performance parameters at design conditions as a reference point to derive the corresponding performance characteristics at numerous suction conditions with less dependency on the geometrical features. Through a case study on a gas transport centrifugal compressor, it was found that the developed approach can be applied for design evaluation on the expected variation of working conditions, and for the operation diagnosis of installed units as well. Furthermore, a parametric study has been conducted to investigate the effect of gas properties on the stage efficiency, surge margin, and compressor structure. The obtained results support the need for considering the gas properties variation when the off-design performance is derived. To evaluate the impact of internal blockage on the performance parameters, this study proposed an approach to model the effect of non-reactive deposits, which has been qualified using four operation cases and the obtained results are compared with the internal inspection findings from the stage overhauling process. This also covers the influential aspects of flow blockage on the technical and economic values. Since the main challenge here is to analyze the process gas composition in real time, the influences of the non-reactive deposits have been compared with the effect of the unanticipated gas composition change. Subsequently, it has turned out that the pressureratio parameter is not enough to assess the possibility of flow blockage and unexpected gas properties change. Moreover, it was observed that the stage discharge pressure was more sensitive to the fouled aftercooler comparing with suction and internal blockage. However, the effect of contaminated aftercooler on the surge point and discharge pressure and temperature of the upstream stage was found greater than its impact on the shaft power. Thus, a substantial surge margin reduction was detected when the first stage was operating with a fouled aftercooler comparing with the measured reduction as a result of unanticipated gas properties change. Furthermore, a larger pressure ratio drop was measured in the case of liquid carryover which revealed a more significant impact of the two phases densities difference comparing with the gas volume fraction (GVF) effect. The possibility of hydrate formation has been assessed using hydrate formation temperature (HFT) criteria. Additionally, this research highlights a number of challenges facing the selection of typical centrifugal stage design by assessing the contribution of design characteristics on the operating efficiency and stable flow range. Besides, an empirical-based-model was established to select the optimum impeller and diffuser configurations in order to make a compromise decision based on technical and economic perspective. It was concluded that there is no absolute answer to the question of optimum rotor and stator configuration. The preliminary aerothermodynamic evaluation exposed that the selection of the optimum impeller structure is governed by several variables: stage efficiency, pressure loss coefficient, manufacturing cost, required power cost, resonance frequency and stable operating range. Hence, an evaluation is required to compromise between these parameters to ensure better performance. Furthermore, it was argued throughout this study that the decision-making process of the typical stage geometrical features has to be based upon the long-term economic performance optimization. Thus, for higher long-term economic performance, it is not sufficient to select the characteristics of the impeller and diffuser geometry based on the low manufacturing cost or efficiency improvement criterion only. For turboexpanders, a simple and low cost tool has been developed to determine the optimum turboexpander characteristics by analysing the generated design alternatives. This approach was used in designing a turboexpander for hydrocarbon liquefaction process. Moreover, since the turboexpanders are expected to run continuously at severe gas conditions, the performance of the selected turboexpander was evaluated at different inlet flow rates and gas temperatures. It has turned out that designing a turboexpander with the maximum isentropic efficiency is not always possible due to the limitations of the aerodynamic parameters for each component. Therefore, it is necessary to assess the stage geometrical features prior the construction process to compromise between the high capital cost and the high energetic efficiency.
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Thiagarajan, Manoharan. "A Design Study of Single-Rotor Turbomachinery Cycles." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/10076.

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Gas turbine engines provide thrust for aircraft engines and supply shaft power for various applications. They consist of three main components. That is, a compressor followed by a combustion chamber (burner) and a turbine. Both turbine and compressor components are either axial or centrifugal (radial) in design. The combustion chamber is stationary on the engine casing. The type of engine that is of interest here is the gas turbine auxiliary power unit (APU). A typical APU has a centrifugal compressor, burner and an axial turbine. APUs generate mechanical shaft power to drive equipments such as small generators and hydraulic pumps. In airplanes, they provide cabin pressurization and ventilation. They can also supply electrical power to certain airplane systems such as navigation. In comparison to thrust engines, APUs are usually much smaller in design. The purpose of this research was to investigate the possibility of combining the three components of an APU into a single centrifugal rotor. To do this, a set of equations were chosen that would describe the new turbomachinery cycle. They either were provided or derived using quasi-one-dimensional compressible flow equations. A MathCAD program developed for the analysis obtained best design points for various cases with the help of an optimizer called Model Center. These results were then compared to current machine specifications (gas turbine engine, gasoline and diesel generators). The result of interest was maximum specific power takeoff. The results showed high specific powers in the event there was no restriction to the material and did not exhaust at atmospheric pressure. This caused the rotor to become very large and have a disk thickness that was unrealistic. With the restrictions fully in place, they severely limited the performance of the rotor. Sample rotor shapes showed all of them to have unusual designs. They had a combination of unreasonable blade height variations and very large disk thicknesses. Indications from this study showed that the single radial rotor turbomachinery design might not be a good idea. Recommendations for continuation of research include secondary flow consideration, blade height constraints and extending the flow geometry to include the axial direction.
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Leng, Yujun. "Preliminary design tools in turbomachinery| Non-uniformly spaced blade rows, multistage interaction, unsteady radial waves, and propeller horizontal-axis turbine optimization." Thesis, Purdue University, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10149746.

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Turbomachinery flow fields are inherently unsteady and complex which makes the related CFD analyses computationally intensive. Physically based preliminary design tools are desirable for parametric studies early in the design stage, and to provide deep physical insight and a good starting point for the later CFD analyses. Four analytical/semi-analytical models are developed in this study: 1) a generalized flat plate cascade model for investigating the unsteady aerodynamics of a blade row with non-uniformly spaced blades; 2) a multistage interaction model for investigating rotor-stator interactions; 3) an analytical solution for quantifying the impeller wake convection and pressure wave propagating between a centrifugal compressor impeller and diffuser vane; and 4) a semi-analytical model based Lifting line theory for unified propeller and horizontal-axis turbine optimization. Each model has been thoroughly validated with existing models.

With these models, non-uniformly spaced blade rows and vane clocking are investigated in detail for their potential use as a passive control technique to reduce forced response, flutter and aeroacoustic problems in axial compressors. Parametric studies with different impeller blade numbers and back sweep angles are conducted to investigate their effect on impeller wake and pressure wave propagation. Results show that the scattered pressure waves with high circumferential wave numbers may be an important excitation source to the impeller as their amplitude grows much faster as they travel inwardly than the lower order primary pressure waves. Detailed analysis of Lifting line theory reveals the mathematical and physical equivalence of Lifting line models for propellers and horizontal-axis turbines. With a new implementation, the propeller optimization code can be used for horizontal-axis turbine optimization without any modification. The newly developed unified propeller and horizontal-axis turbine optimization code based on lifting line theory and interior point method has been shown to be a very versatile tool with the capability of hub modelling, working with non-uniform inflow and including extra user specified constraints.

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Zangeneh-Kazemi, Mehrdad. "Three-dimensional design of radial-inflow turbines." Thesis, University of Cambridge, 1989. https://www.repository.cam.ac.uk/handle/1810/250944.

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The main part of this dissertation is concerned with the development of a fully three dimensional compressible inverse design method, suitable for the design of radial-inflow turbines and other turbomachines with arbitrary meridional geometry. The basic idea of the method is to represent the action of the blades by sheets of vorticity whose strength is determined from prescribed distribution of rVθ (or circulation 2πrVθ). The flow is assumed subsonic and inviscid and the blades are assumed to have negligible thickness. But the blade blockage effects are approximately accounted for by using a mean streamsurface thickness parameter in the continuity equation. As a first approach, the pitchwise variation of density was neglected and the problem was solved by using an approximate form of the continuity equation. Simple expressions were derived for the terms neglected in the approximate continuity equation. The problem was also solved by using the exact form of the continuity equation and the results of the approximate and exact methods were compared for a number of test cases. The comparison showed that the approximate method can compute the blade shape accurately. A small high (subsonic) speed radial-inflow turbine was designed by the new method. In order to assess the accuracy of the method, the flow through the designed impeller was computed by three dimensional inviscid and viscous flow analysis programs and good correlation was obtained between the computed and specified rVθ distributions. The designed impeller was manufactured and its performance was measured and compared to three other baseline impellers, one conventional and two experimental. The new impeller performed substantially better than all the baseline turbines and showed a 5.5% improvement over the conventional impeller. However, only 2.5% of this improvement was attributed to the aerodynamically superior blade shape designed by the new method. An appreciable improvement in efficiency was also observed at off-design conditions. Finally, the presence of a, generally observed, high loss region near the shroud at exit of radial-inflow turbines was investigated and it was found that secondary flow is the basic mechanism behind this phenomenon.
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Ji, Min. "Fully three-dimensional and viscous semi-inverse method for axial/radial turbomachine blade design." Related electronic resource: Current Research at SU : database of SU dissertations, recent titles available full text, 2008. http://wwwlib.umi.com/cr/syr/main.

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Vijayaraj, K. "Thermal Turbomachinery Design for Closed Thermal Cycles and Multiple Fluids." Thesis, 2020. https://etd.iisc.ac.in/handle/2005/4640.

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Closed-cycle gas turbines can complement conventional power conversion systems due to their potential for improved efficiencies, compact system layouts, and the ability to exploit non-fossil fuel energy sources which leads to low carbon emissions. Moreover, they can be adopted for distributed power generation applications. This thesis provides an understanding of the true essence of closed-cycle gas turbines with a focus on the development of turbomachinery design methodologies. The methodologies have been applied for the radial turbomachinery design (small-scale power range) for supercritical Brayton cycles and other thermal cycles such as air cycle, organic Rankine cycle, cryogenic cycles, and steam Rankine cycle. The thesis begins with an elaborate review of the potential of closed-cycle gas turbines. Thermodynamic analysis has been carried out for the recuperated closed Brayton cycle with and without intercooling employing different working fluids. It has shown that the supercritical carbon dioxide gives considerably higher efficiencies at mild turbine inlet temperatures of 400-700°C and helium can be considered at higher temperatures of above 800°C. The closed Brayton cycle turbomachinery designs with multiple fluids have been brought together uniquely on two charts, one in absolute scale (∆H-M-D) and other in non-dimensional scale (NS-DS) by carrying out a detailed survey of the closed-cycle gas turbine plants and concept designs, which can aid in the design of turbines and compressors for different applications. Turbomachinery design can have two approaches. The first one is scaling a benchmark design for different fluids catering to a particular application. The second one is a thorough step-by-step meanline design methodology for both turbines and compressors for any new application. Turbomachinery development through scaling a good benchmark design using the power of similitude to adapt it to the different working fluids employed in various thermal cycles can save considerable amount of time and provide a quick solution with good performance. The scaling methodology has been used for the development of radial turbomachinery for a 50 kW supercritical carbon dioxide (SCO2) power plant. The CFD simulations along with experimental results have confirmed that the scaling technique is quite good. The radial inflow turbine had an isentropic efficiency of 77 % from the CFD simulation at the design point with SCO2 fluid. The torque coefficients, flow coefficients, and the efficiencies determined from the CFD simulations for the turbine, when superimposed on the benchmark turbine experimental curves, showed good agreement. The efficiencies for the compressor from CFD with SCO2 fluid were lower compared to the experimental efficiencies of the benchmark compressor, but the curves showed the same trend. The highest CFD efficiency of 77.2 % was obtained at a flow coefficient of around 0.46. Experiments were carried out for the developed turbine and compressor assembly using air as the fluid (aeroloop) to mainly observe the vibrations at high speeds. The assembly had run-up to a maximum speed of 70000 rpm. The turbine flow coefficients from the aeroloop experiment were not far away from the simulation and the NASA benchmark data. The compressor flow coefficient zone from the experiment coincided with the flow coefficient zone of open-type boundary condition simulation results of the compressor with air as the fluid. Also, the absolute plot of speed vs. mass flow rate for the compressor in the aeroloop test matched well with the open boundary type CFD simulation results. The thesis has also presented a scaling procedure to develop turboexpanders from a benchmark air turbine having experimental characteristics. It has been applied for the design of turboexpanders for supercritical carbon dioxide (SCO2) Brayton cycle, R143a organic Rankine cycle, and helium cryogenic cycle. The dimensionless iso-Mach number characteristic curves and efficiency curves of the SCO2 turbine, helium turbine, and R143a turbine determined from the CFD simulations were superimposed on the experimental characteristics of the benchmark turbine. There was good conformance between both, which proved that the proposed scaling methodology can be adopted for the turboexpander design. Detailed meanline design procedures were proposed in this thesis for radial inflow turbine and centrifugal compressor using specific speed and specific diameter parameters so that the design can be started from scratch for a new application. These were used for the development of a turbo-compressor for the 2 kW air cycle machine for DARE (DRDO) which is employed in aircraft cooling. The radial inflow turbine had an isentropic total efficiency of 85.6 %. The centrifugal compressor designed based on the proposed methodology had an isentropic total efficiency of 76 %. Another design of centrifugal compressor which was carried out in a different approach had attained an efficiency of 78.6 %. Radial turbomachinery design for a 1 MW supercritical carbon dioxide power plant has been presented in which the radial turbine is designed using the proposed 1-D meanline design methodology and the centrifugal compressor is designed using the scaling school of thought. Numerical simulations showed isentropic total efficiencies of 91% for the radial inflow turbine and 77.25 % for the centrifugal compressor at the design point. The last part of the thesis has discussed the design procedure of an unconventional turbine type called ‘radial outflow turbine’ for a 200 kW steam Rankine cycle and 1 MW supercritical carbon dioxide Brayton cycle. The design point CFD simulation of the 18-stage steam radial outflow turbine showed efficiency close to 75 %. A new zone was identified for the radial outflow turbine in Balje’s specific speed-specific diameter chart. The design point CFD efficiency of the supercritical carbon dioxide radial outflow turbine was 84.6 %.
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Books on the topic "Radial Turbomachinery design"

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1913-, Hawthorne William Sir, and United States. National Aeronautics and Space Administration., eds. Three-dimensional flow in radial turbomachinery and its impact on design. Cambridge, MA: Gas Turbine Laboratory, Dept. of Aeronautics and Astronautics, Massachusetts Institute of Technology, 1993.

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United States. National Aeronautics and Space Administration., ed. Enhanced analysis and users manual for radial-inflow turbine conceptual design code RTD. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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3

Whitfield, A. Design of radial turbomachines. Harlow, Essex, England: Longman Scientific & Technical, 1990.

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ASME. Print Proceedings of the ASME Turbo Expo 2018 : Turbomachinery Technical Conference and Exposition : Volume 2B : Turbomachinery : Axial Flow Turbine Aerodynamics; Turbomachinery : Noise, Ducts and Interactions; Turbomachinery: Radial Turbomachinery Aerodynamics. American Society of Mechanical Engineers, The, 2018.

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Three-dimensional flow in radial turbomachinery and its impact on design. Cambridge, MA: Gas Turbine Laboratory, Dept. of Aeronautics and Astronautics, Massachusetts Institute of Technology, 1993.

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Three-dimensional flow in radial turbomachinery and its impact on design. Cambridge, MA: Gas Turbine Laboratory, Dept. of Aeronautics and Astronautics, Massachusetts Institute of Technology, 1993.

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National Aeronautics and Space Administration (NASA) Staff. Three-Dimensional Flow in Radial Turbomachinery and Its Impact on Design. Independently Published, 2019.

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Whitfield, A., and N. C. Baines. Design of Radial Turbomachines. Longman, 1990.

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Book chapters on the topic "Radial Turbomachinery design"

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Macchi, Ennio. "The Use of Radial Equilibrium and Streamline Curvature Methods for Turbomachinery Design and Prediction." In Thermodynamics and Fluid Mechanics of Turbomachinery, 133–66. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_4.

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Roy, Apurba Kumar, Supriyo Roy, and Kaushik Kumar. "Strategic Designing and Optimization of Mixed Flow Impeller Blades for Maritime Applications." In Handbook of Research on Military, Aeronautical, and Maritime Logistics and Operations, 470–508. IGI Global, 2016. http://dx.doi.org/10.4018/978-1-4666-9779-9.ch025.

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Mixed flow impellers are extensively used in turbomachines either to convert mechanical energy to fluid energy or to convert fluid energy to mechanical energy. According to the geometry of flow passage, turbo machines can be classified as radial, axial and mixed flow. Mixed flow turbomachines are widely used for engineering applications like cooling water duties, water intake impellers for maritime applications, flood water draining, irrigation and other application fields. The design of mixed flow impellers of high specific speed is a direct extension of the well-established methods of the designing of radial flow impellers but the introduction of near diagonal flow layout at a still larger specific speed stimulated the incorporation of axial impeller design techniques in mixed flow impeller technology. Here, an attempt has been made to design a mixed flow turbo machine blade from the basic principle of turbomachinery and fluid mechanics. On the basis of stress analysis, the blade positioning in the meridional annulus was selected and validated using artificial neural network.
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"Design methods for radial-flow turbomachines." In The Design of High-Efficiency Turbomachinery and Gas Turbines. The MIT Press, 2014. http://dx.doi.org/10.7551/mitpress/9940.003.0016.

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Conference papers on the topic "Radial Turbomachinery design"

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Ludewig, Alexander, Gunther Brenner, and Kathrin Skinder. "DMD Analysis of Radial Turbomachinery." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82953.

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Abstract In the design of turbomachinery, the avoidance of flow-induced vibrations offers optimisation potential with regard to noise reduction and the extension of the service life of a machine. To achieve this, damage-relevant should be analyzed in the development phase using methods such as forced response or flutter calculations. A forced response analysis requires the specification of flow-induced excitations in the spectral range, which can be obtained from a temporal numerical simulation using FFT. Since the FFT depends on the time span and therefore only reproduces discrete frequencies, only rotational frequencies and their integer harmonics can be determined from a single rotational period. To work around this, a Dynamic Mode Decomposition (DMD) is applied to analyse the flow field in a high performance centrifugal fan obtained from simulation and measurement data. DMD is a model order reduction method based on singular value decomposition. It extracts modes and eigenvalues of a nonlinear, dynamic system. DMD is considered an ideal combination of proper orthogonal decomposition in space and Fourier transform in time. The numerical data were generated with a CFD calculation based on the unsteady Reynolds-averaged Navier-Stokes equations together with the k-ω SST turbulence model. As a result of this study, it can be shown that the DMD agrees exactly with the analysis of the FFT based on transient local pressure sensors. For the two-dimensional pressure field, however, the DMD deviates significantly from the FFT in the amplitudes for higher-frequency excitations, partly showing better agreement with the measurements of the pressure sensors.
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Cox, Graham D. "Design Point Efficiency of Radial Turbines." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75533.

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Results are presented from CFD calculations on a large database of 3D, radially-stacked, radial turbine geometries. The database covers a comprehensive range of basic geometrical features allowing the most appropriate geometry to be selected for optimum efficiency over extensive ranges of blade-speed-ratio, flow coefficient and specific speed. Initial studies considered the wheel only and used 78 geometries for low Mach number applications and 102 geometries for high Mach number applications. Each was run over a range of blade-speed-ratios and inlet flow angles to generate preliminary results. Designs that did not contribute to the optimum efficiency trends were discarded. The remaining 17 low Mach number and 24 High Mach number wheels were recalculated with a range of nozzle guide vanes and back-face cavities to provide increased fidelity numerical solutions. The calculated optimum efficiency is presented on charts of blade-speed-ratio against flow coefficient, against specific speed and against non-dimensional mass-flow. The effect of exducer trim reduction, as often required for mechanical reasons, is demonstrated. The charts can be used for preliminary design of new applications.
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Cravero, Carlo. "A Design Methodology for Radial Turbomachinery: Application to Turbines and Compressors." In ASME 2002 Joint U.S.-European Fluids Engineering Division Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/fedsm2002-31335.

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Different design/analysis tools are combined in an automatic procedure for the design of radial turbomachinery. The algorithms developed have different complexity levels ranging from the meanline one-dimensional design tool to the fully three-dimensional Navier-Stokes based analysis. Each code gives complementary information to the designer. The codes have been written and developed by the author at DIMSET. The design procedure is developed for both radial compressors and turbines and it is proposed for the dimensioning of rotating machinery for microgasturbine power plants.
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Inhestern, Lukas Benjamin, James Braun, Guillermo Paniagua, and José Ramón Serrano Cruz. "Design, Optimization and Analysis of Supersonic Radial Turbines." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91756.

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Abstract New compact engine architectures such as pressure gain combustion require ad-hoc turbomachinery to ensure an adequate range of operation with high performance. A critical factor for supersonic turbines is to ensure the starting of the flow passages, which limits the flow turning and airfoil thickness. Radial outflow turbines inherently increase the cross section along the flow path, which holds great potential for high turning of supersonic flow with a low stage number and guarantees a compact design. First the preliminary design space is described. Afterwards a differential evolution multi-objective optimization with 12 geometrical design parameters is deducted. With the design tool AutoBlade 10.1, 768 geometries were generated and hub, shroud, and blade camber line were designed by means of Bezier curves. Outlet radius, passage height, and axial location of the outlet were design variables as well. Structured meshes with around 3.7 million cells per passage were generated. Steady three dimensional Reynolds averaged Navier Stokes (RANS) simulations, enclosed by the k-omega SST turbulence model were solved by the commercial solver CFD++. The geometry was optimized towards low entropy and high power output. To prove the functionality of the new turbine concept and optimization, a full wheel unsteady RANS simulation of the optimized geometry exposed to a nozzled rotating detonation combustor (RDC) has been performed and the advantageous flow patterns of the optimization were also observed during transient operation.
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Hassan, Ahmed Farid Saad Ayad, Christopher Fuhrer, Markus Schatz, and Damian Vogt. "Multi-channel casing design for radial turbine operation control." In European Conference on Turbomachinery Fluid Dynamics and Thermodynamics. European Turbomachinery Society, 2019. http://dx.doi.org/10.29008/etc2019-021.

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Leto, Angelo. "Radial Turbine Global Design for Liquid Rocket Engine Application." In European Conference on Turbomachinery Fluid Dynamics and Thermodynamics. European Turbomachinery Society, 2019. http://dx.doi.org/10.29008/etc2019-324.

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Kirk, R. G. "Evaluation of AMB Turbomachinery Auxiliary Bearings." In ASME 1997 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/detc97/vib-4059.

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Abstract The use of active magnetic bearings (AMB) for turbomachinery has experienced substantial growth during the past two decades. The advantages for many applications make AMB’s a very attractive solution for potentially low loss and efficient support for both radial and thrust loads. New machinery must be shop tested prior to shipment to the field for installation on-line. For AMB turbomachinery, one additional test is the operation of the auxiliary drop or overload bearings. A major concern is ability of the selected auxiliary bearing to withstand the contact forces following an at speed rotor drop. The proper design of AMB machinery requires the calculation of the anticipated loading for the auxiliary bearings. Analytical techniques to predict the rotor transient response are reviewed. Results of transient response evaluation of a full-size compressor rotor are presented to illustrate some of the important parameters in the design for rotor drop.
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Wang, Xuesong, Jinju Sun, Changjiang Huo, Guilong Huo, and Peng Song. "Design and Flow Analysis of a Radial Outflow Turbo-Expander." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90346.

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Abstract Radial-outflow turbo-expanders have emerged in the recent years to suit some special applications where complex multi-phase and multi-component flows (like liquid-rich gases and solid particle-laden gases) need to be expanded. This paper presents a systematic study on the design and flow behavior of a single stage radial-outflow turbo-expander, which is to be used in organic Rankine power system to covert the low-temperature heat into shaft power. A mean-line code coupled with the optimization algorithm is developed and used to carry out the one-dimensional preliminary design, where 7 non-dimensional parameters are used as design variables (nozzle velocity coefficient, rotor velocity coefficient, reaction, rotor inlet and outlet flow angles, velocity ratio, and rotor diameter ratio). In comparison with the original design, significant design performance gains are achieved with the matched combination of design parameters. Geometric shape design is further performed for the expander. In consideration of the flow features in nozzle and rotor blade passages being nearly two-dimensional, blade shape design of both rows is conducted on the basis of the airfoils used for conventional axial flow turbines, where a conformal mapping method is used to convert the axial profile into the polar coordinate frame and it is then represented by 11 parameters of mean cylindrical diameter, radial and tangential chord, leading and trailing edge radius, blade inlet and outlet angles, blade inlet wedge angle, number of blades, unguided turning, and throat size. Flow and overall performance are simulated and predicted for the designed expander, where the output shaft power and overall isentropic efficiency is respectively predicted as 87.86 kW and 81.60% at design condition.
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da Silva, Edna Raimunda, Konstantinos G. Kyprianidis, Michael Säterskog, Ramiro G. Ramirez Camacho, and Angie L. Espinosa Sarmiento. "Preliminary Design Optimization of an Organic Rankine Cycle Radial Turbine Rotor." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64028.

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The present study describes the application of a preliminary design approach for the optimization of an organic Rankine cycle radial turbine. Losses in the nozzle the rotor have initially been modelled using a mean-line design approach. The work focuses on a typical small-scale application of 50 kW, and two working fluids, R245fa (1,1,1,3,3,-pentafluoropropane) and R236fa (1,1,1,3,3,3-hexafluoropropane) are considered for validation purposes. Real gas formulations have been used based on the NIST REFPROP database. The validation is based on a design from the literature, and the results demonstrate close agreement the reference geometry and thermodynamic parameters. The total-to-total efficiencies of the reference turbine designs were 72% and 79%. Following the validation exercise, an optimization process was performed using a controlled random search algorithm with the turbine efficiency set as the figure of merit. The optimization focuses on the R245fa working fluid since it is more suitable for the operating conditions of the proposed cycle, enables an overpressure in the condenser and allows higher system efficiency levels. The R236fa working fluid was also used for comparison with the literature, and the reason is the positive slope of the saturation curve, somehow is possible to work with lower temperatures. Key preliminary design variables such as flow coefficient, loading coefficient, and length parameter have been considered. While several optimized preliminary designs are available in the literature with efficiency levels of up to 90%, the preliminary design choices made will only hold true for machines operating with ideal gases, i.e. typical exhaust gases from an air-breathing combustion engine. For machines operating with real gases, such as organic working fluids, the design choices need to be rethought and a preliminary design optimization process needs to be introduced. The efficiency achieved in the final radial turbine design operating with R245fa following the optimization process was 82.4%. A three-dimensional analysis of the flow through the blade section using computational fluid dynamics was carried out on the final optimized design to confirm the preliminary design and further analyze its characteristics.
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Honavara Prasad, Srikanth, and Daejong Kim. "Scaling Laws of Radial Clearance and Bump Stiffness of Radial Foil Bearings." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56704.

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Design and analysis of foil bearings involve consideration to various physical aspects such as fluid pressure, structural deformation and heat generation due to viscous effects within the bearing. These complex physical interactions are mathematically governed by highly nonlinear partial differential equations. Therefore, foil bearing design involves detailed calculations of flow fields (velocities, pressures), bump deflections (structural compliance) and heat transfer phenomena (viscous dissipation in the fluid, frictional heating, temperature profile etc.). The computational effort in terms of time and hardware requirements make high level engineering analyses tedious which presents an opportunity for development of rule of thumb laws for design guidelines. Scaling laws for bearing clearance and bump stiffness of radial foil bearings of various sizes are presented in this paper. The scaling laws are developed from first principles using the scale invariant Reynolds equation and bump deflection equation. Power law relationships are established between the 1) radial clearance and bearing radius and 2) bump stiffness and bearing radius. Simulation results of static and dynamic performance of various bearing sizes following the proposed scaling laws are presented.
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