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Journal articles on the topic 'Turbomachine design'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

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.

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Chaves-Jacob, Julien, Gérard Poulachon, Emmanuel Duc, and Christian Geffroy. "Design for manufacturing applied to turbomachine components." International Journal of Advanced Manufacturing Technology 57, no. 5-8 (2011): 453–63. http://dx.doi.org/10.1007/s00170-011-3306-6.

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3

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 (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 exa

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Weickgenannt, Ansgar, Ivan Kantor, François Maréchal, and Jürg Schiffmann. "On the Application of Small-Scale Turbines in Industrial Steam Networks." Energies 14, no. 11 (2021): 3149. http://dx.doi.org/10.3390/en14113149.

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This study investigates the technical and economic feasibility of replacing throttling valves with smale-scale, oil-free turbomachinery in industrial steam networks. This is done from the perspective of the turbomachine, which has to be integrated into a new or existing process. The considered machines have a power range of P=[0.5,…,250 kW] and have been designed using real industrial data from existing processes. Design guidelines are developed, which take into account the thermodynamic process as well as engineering aspects of such a turbomachine. The results suggest that steam conditioning

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Sun, Shao Chun, and Geng Chen Shi. "Design, Simulation and Fabrication of an Air-Driven Microturbomachine." Key Engineering Materials 483 (June 2011): 611–15. http://dx.doi.org/10.4028/www.scientific.net/kem.483.611.

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This paper presents the design, simulation and fabrication of an mm-scale air-driven microturbomachine. The circumferential-flow turbomachine has a plain-shaped structure with an overall size of 8×8×3mm3. The predicted formulas for driving torque and driving power are deduced by analyzing the working condition of the model. Finite element simulation is carried out to determine the driving torque and driving power. Turbine and stator are fabricated using UV-LIGA technique, while other components using pension micromachining. Test results of assembled prototype show that under the air-flow speed

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Makarov, Vladimir, Nikolai Makarov, Alexandr Lifanov, Artem Materov, and Nikolay Kosarev. "Aerodynamic adaptivity criterion in the production methodology of the energy-efficient mine turbomachines." E3S Web of Conferences 177 (2020): 03004. http://dx.doi.org/10.1051/e3sconf/202017703004.

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Competitive growth of enterprises in the mining and oil and gas industries of the Russian economy, combined with industrial safety requirements, updates the task of developing the design and production methodology for the aerodynamically adaptive turbomachines with a nature-like dominance. Such machines adequately and economically soundly establish the necessary parameters of the air environment in the technological space that implement the concept of optimal subsurface management ecotechnology. This article proposes a production methodology for the energy-efficient turbomachines using the aer

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Kalinkevych, Mykola, Oleksandr Gusak, Andriy Skoryk, and Oleg Shcherbakov. "Design and Flow Parameters Calculation of the Turbomachine Channels." Procedia Engineering 39 (2012): 275–85. http://dx.doi.org/10.1016/j.proeng.2012.07.034.

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8

Xu, C., and R. S. Amano. "On the Development of Turbomachine Blade Aerodynamic Design System." International Journal for Computational Methods in Engineering Science and Mechanics 10, no. 3 (2009): 186–96. http://dx.doi.org/10.1080/15502280902795052.

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Makarov, Vladimir, Gennadii Boiarskikh, Nikolai Makarov, German Dyldin, and Aleksandr Ugolnikov. "Turbomachine criteria for similarity of natural size proportionality." Izvestiya vysshikh uchebnykh zavedenii Gornyi zhurnal 1, no. 8 (2020): 81–89. http://dx.doi.org/10.21440/0536-1028-2020-8-81-89.

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Introduction. It is possible to give rise to synergy as a result of science-intensive industries combination with innovative eco-technologies for subsoil use only by developing a brand new approach to nature-like auxiliary technologies. Insufficient adaptability of turbomachines that ensure industrial safety increases the production cost of the mining and oil and gas complexes of the Russian Federation by more than 15%, reducing its competitiveness. Research methodology. Based on the hypothesis of the hydrodynamic analogy of the mechanisms of deceleration of the flow around the airfoil and the

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10

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 (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 h

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Dykas, Brian, and Samuel A. Howard. "Journal Design Considerations for Turbomachine Shafts Supported on Foil Air Bearings." Tribology Transactions 47, no. 4 (2004): 508–16. http://dx.doi.org/10.1080/05698190490493391.

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Ntoko, Nzumbe-Mesape, and W. G. Cartwright. "Design of axial turbomachine blade camber surfaces using the Bézier technique." Computer-Aided Design 18, no. 6 (1986): 316–18. http://dx.doi.org/10.1016/0010-4485(86)90093-x.

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13

Jiang, J., and T. Dang. "Design Method for Turbomachine Blades With Finite Thickness by the Circulation Method." Journal of Turbomachinery 119, no. 3 (1997): 539–43. http://dx.doi.org/10.1115/1.2841155.

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This paper presents a procedure to extend a recently developed three-dimensional inverse method for infinitely thin blades to handle blades with finite thickness. In this inverse method, the prescribed quantities are the blade pressure loading and the blade thickness distributions, and the calculated quantity is the blade mean camber line. The method is formulated in the fully inverse mode whereby the blade shape is determined iteratively using the flow-tangency condition along the blade surfaces. Design calculations are presented for an inlet guide vane, an impulse turbine blade, and a compre

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Mandel, Savannah. "Wake-blade and wake-wake interactions shed light on turbomachine design optimization." Scilight 2019, no. 50 (2019): 501109. http://dx.doi.org/10.1063/10.0000389.

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Kodochigov, N. G., V. F. Golovko, and M. E. Ganin. "Turbomachine design choice for the gas-turbine cycle of NPP with HTGR." Atomic Energy 114, no. 2 (2013): 108–14. http://dx.doi.org/10.1007/s10512-013-9679-x.

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Shan, Peng. "A mass addition approach to the bypass turbomachine through flow inverse design problem." Journal of Mechanical Science and Technology 22, no. 10 (2008): 1921–25. http://dx.doi.org/10.1007/s12206-008-0733-x.

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Xu, J. Z., and C. W. Gu. "A Numerical Procedure of Three-Dimensional Design Problem in Turbomachinery." Journal of Turbomachinery 114, no. 3 (1992): 548–52. http://dx.doi.org/10.1115/1.2929178.

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A numerical method for solving the three-dimensional aerothermodynamic design problem with some type of Mach number distributions on the blade surfaces is presented. In the usual aerothermodynamic design of a turbomachine, the three-dimensional coordinates of the blade are attained through stacking of the cascade profiles and may not ensure the desired velocity distribution. To avoid this problem, the present method will give new coordinates of the blade according to the required Mach number distribution. The method is based on the pseudostream function formulation and the treatment of the bou

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18

Varney, Philip, and Itzhak Green. "Dynamic modeling of an eccentric face seal including coupled rotordynamics, face contact, and inertial maneuver loads." Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology 232, no. 6 (2017): 732–48. http://dx.doi.org/10.1177/1350650117727230.

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Mechanical face seals are constitutive components of turbomachines, which in turn can be constitutive to other systems (e.g. aircraft). Furthermore, the rotating element of a face seal is inextricably coupled to the turbomachine via a flexible mount, and the stationary seal element is coupled to the rotating seal element via the fluid film existing between the seal faces. Consequentially, understanding interactions between the seal and turbomachine is important for quantifying seal performance and improving its design. With few exceptions, previous works study the face seal dynamics independen

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19

Li, Le, and Huoxing Liu. "The Analysis of Leading Edge Deformations on Turbomachine Blades." Energies 12, no. 4 (2019): 736. http://dx.doi.org/10.3390/en12040736.

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With recent advancements in the development of material and manufacturing technology, the leading edge geometry of turbomachine blades has attracted widespread attention. “Sharp” leading edges always have a better aerodynamic performance, though it is prone to deformations easily. Thus, flat plates and real compressor cascades with different leading edge deformations were investigated to study the influence, which is applicable for thin blades at low speeds. Different boundary layer characteristics, including the velocity profile, transition process, and loss, are compared. The results show th

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Liu, Haoran, Yeming Lu, Jinguang Yang, et al. "Aeroacoustic Optimization of the Bionic Leading Edge of a Typical Blade for Performance Improvement." Machines 9, no. 8 (2021): 175. http://dx.doi.org/10.3390/machines9080175.

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New, innovative optimization approaches to improve turbomachine performance and reduce turbomachine noise are significant in engineering. In this paper, based on the bionic concept, a wave structure is used to shape the leading edge of the blade. Using an NACA0018 blade as the basic blade, a united parametric approach controlled by three parameters is proposed to configure the wavy leading edge. Then, a new optimization strategy boosting design efficiency is established to output the optimal design results. Finally, the corresponding performance and flow mechanism are analyzed. Taking into acc

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21

Wang, Jinxin, Toshiyuki Nakata, and Hao Liu. "Development of Mixed Flow Fans with Bio-Inspired Grooves." Biomimetics 4, no. 4 (2019): 72. http://dx.doi.org/10.3390/biomimetics4040072.

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Mixed flow fan is a kind of widely used turbomachine, which has faced problems of further performance improvement in traditional design methods in recent decades. Inspired by the microgrooves such as riblets and denticles on bird feathers and shark skins, we here propose biomimetic designs of various blades with the bio-inspired grooves, aiming at the improvement of the aeroacoustic performance. Based on a systematic study with computational fluid dynamic analyses, we found that these designs had the potential in noise suppression even with macroscopic grooves. Our best design can suppress tur

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22

Chi, R. M., and A. V. Srinivasan. "Some Recent Advances in the Understanding and Prediction of Turbomachine Subsonic Stall Flutter." Journal of Engineering for Gas Turbines and Power 107, no. 2 (1985): 408–17. http://dx.doi.org/10.1115/1.3239741.

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In this paper, some recent advances in the understanding and prediction of subsonic flutter of jet engine fan rotor blades are reviewed. Among the topics discussed are (i) the experimental evidence of mistuning in flutter responses, (ii) new and promising unsteady aerodynamic models for subsonic stall flutter prediction, (iii) an overview of flutter prediction methodologies, and (iv) a new research effort directed toward understanding the mistuning effect on subsonic stall flutter of shrouded fans. A particular shrouded fan of advanced design is examined in the detailed technical discussion.

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23

Dang, T. Q. "A Fully Three-Dimensional Inverse Method for Turbomachinery Blading in Transonic Flows." Journal of Turbomachinery 115, no. 2 (1993): 354–61. http://dx.doi.org/10.1115/1.2929241.

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This paper presents a procedure to extend a recently developed fully three-dimensional inverse method for highly loaded turbomachine blades into the transonic-flow regime. In this inverse method, the required three-dimensional blade profile to produce a prescribed swirl schedule is determined iteratively using the blade boundary conditions. In the present implementation, the flow is assumed to be inviscid and the blades are assumed to be infinitely thin. The relevant equations are solved in the conservative forms and are discretized in all three directions using a finite-volume technique. Calc

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KUCHERENKO, VALERI V., and JULIO C. GÓMEZ-MANCILLA. "BIFURCATIONS OF AN EXACTLY SOLVABLE MODEL OF ROTORDYNAMICS." International Journal of Bifurcation and Chaos 10, no. 12 (2000): 2689–99. http://dx.doi.org/10.1142/s0218127400001730.

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Diverse cyclic responses for an effective and useful nonlinear rotor-bearing-seal system model are studied. In this work two typical cases of self-excited vibrations in turbomachinery are considered: steamwhirl and oilwhip. The first one is an aerodynamic phenomenon induced by the flow of the working fluid at the disc power stages, this excitation being directly proportional to the turbomachine out/input power. The second excitation, oilwhip, is produced by a rotating motion of the lubricating oil film inside the bearings; its magnitude is proportional to the operating speed of the rotor. The

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TOYOKURA, Tomitaro, Toshiaki KANEMOTO, and Moriaki HATTA. "Studies on circular cascades for return channel of centrifugal turbomachine. 1st report Inverse method and cascade design." Transactions of the Japan Society of Mechanical Engineers Series B 52, no. 473 (1986): 50–58. http://dx.doi.org/10.1299/kikaib.52.50.

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Ramos, Helena M., Mariana Simão, and Kaloyan N. Kenov. "Low-Head Energy Conversion: A Conceptual Design and Laboratory Investigation of a Microtubular Hydro Propeller." ISRN Mechanical Engineering 2012 (February 29, 2012): 1–10. http://dx.doi.org/10.5402/2012/846206.

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Low-head microhydro systems for energy production are becoming accepted because of oil crises and new advances in their design and efficiencies. As this is still a new area for development and experimentation, it is important to test and validate the optimal conditions and the hydrodynamic behaviour of such systems under different conditions. The aim of this paper is to present a turbine design validation practise, which researchers and equipment manufactures can use for the hydrodynamic behaviour analysis of new low-head turbines prior to production and application. Laboratory experimental te

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Topp, D. A., and S. Fleeter. "Splitter Blades as an Aeroelastic Detuning Mechanism for Unstalled Supersonic Flutter of Turbomachine Rotors." Journal of Turbomachinery 108, no. 2 (1986): 244–52. http://dx.doi.org/10.1115/1.3262044.

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A mathematical model is developed to demonstrate the application of splitter blades as an aeroelastic detuning mechanism for unstalled supersonic flutter of turbomachine rotors. The splitters introduce both aerodynamic and structural detuning, thereby leading to enhanced aeroelastic stability. The aerodynamic detuning is due to the variable circumferentially spaced splitters between each pair of full chord airfoils, with aerodynamic detuning due to alternate circumferential spacing of the full chord airfoils also considered. The structural detuning arises from the lower natural frequencies of

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Zhao, Xiaolu. "Stream Function Solution of Transonic Flow Along S2 Streamsurface of Axial Turbomachines." Journal of Engineering for Gas Turbines and Power 108, no. 1 (1986): 138–43. http://dx.doi.org/10.1115/1.3239860.

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Based on Wu’s general equations of 3-D turbomachine flow, expressed with respect to nonorthogonal curvilinear coordinates, the conservative stream-function formulations of transonic flow along S2 streamsurface have been discussed. The problem of mixed flow can be solved by the use of the artificial compressibility method, and the passage shock on the S2 streamsurface can be captured. The distribution of the fluid velocity from hub to shroud can be obtained directly by integrating the velocity gradient equation, after the principal equation has been solved, so that the difficulty of the nonuniq

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Coull, John, Christopher Clark, and Raul Vazquez. "The sensitivity of turbine cascade endwall loss to inlet boundary layer thickness." Journal of the Global Power and Propulsion Society 3 (March 26, 2019): OEYMDE. http://dx.doi.org/10.22261/jgpps.oeymde.

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The development of hub and casing boundary layers through a turbomachine is difficult to predict, giving rise to uncertainty in the boundary conditions experienced by each blade row. Previous studies in turbine cascades disagree on the sensitivity of endwall loss to such inlet conditions. This paper explores the problem computationally, by examining a large number of turbine cascades and varying the inlet boundary layer thickness. It is demonstrated that the sensitivity of endwall loss to inlet conditions is design dependent, and determined by the component of endwall loss associated with the

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Nejadali, Jafar. "Calculation of flow in incompressible regenerative turbo-machines with bucket form blades based on the geometry of flow path." International Journal of Numerical Methods for Heat & Fluid Flow 29, no. 8 (2019): 2606–21. http://dx.doi.org/10.1108/hff-10-2018-0595.

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Purpose Regenerative flow pumps are dynamic machines with the ability to develop high heads at low flow rates. Simplicity, compactness, stable features and low manufacturing costs make them interesting for many applications in industries. The purpose of this study is to present a new method for calculating the flow through regenerative pumps with bucket form blades to predict the performance curves by a cheap and easy-to-use way. Design/methodology/approach The analysis was carried out based on the geometric shape of a fluid particle trajectory in a regenerative turbomachine. The fluid particl

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Bonaiuti, Duccio, Andrea Arnone, Mirco Ermini, and Leonardo Baldassarre. "Analysis and Optimization of Transonic Centrifugal Compressor Impellers Using the Design of Experiments Technique." Journal of Turbomachinery 128, no. 4 (2006): 786–97. http://dx.doi.org/10.1115/1.1579507.

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The turbomachine industry is increasingly interested in developing automated design procedures that are able to summarize current design experience, to take into account manufacturing limitations and to define new rules for improving machine performance. In this paper, a strategy for the parametric analysis and optimization of transonic centrifugal impellers was developed, using the technique of the design of experiments coupled with a three dimensional fluid-dynamic solver. The geometrical parameterization was conducted using Bezier curves and a few geometrical parameters, which were chosen a

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Zierer, T. "Experimental Investigation of the Flow in Diffusers Behind an Axial Flow Compressor." Journal of Turbomachinery 117, no. 2 (1995): 231–39. http://dx.doi.org/10.1115/1.2835651.

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The flow fields of four diffusers situated at the rear of a one-stage axial flow compressor were experimentally investigated. Through modification of the compressor operating point, a wide range of variations of the side wall boundary layers and the radial velocity distribution outside of the boundary layers at diffuser inlet could be achieved. The three-dimensional flow field at both diffuser inlet and outlet is analyzed. Changes of inlet blockage and radial velocity distribution and their resulting effects on pressure recovery are thoroughly presented. Compared with the results of measuremen

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Moore, J., and K. M. Elward. "Shock Formation in Overexpanded Tip Leakage Flow." Journal of Turbomachinery 115, no. 3 (1993): 392–99. http://dx.doi.org/10.1115/1.2929266.

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Shock formation due to overexpansion of supersonic flow at the inlet to the tip clearance gap of a turbomachine has been studied. The flow was modeled on a water table using a sharp-edged rectangular channel. The flow exhibited an oblique hydraulic jump starting on the channel sidewall near the channel entrance. This flow was analyzed using hydraulic theory. The results suggest a model for the formation of the jump. The hydraulic analogy between free surface water flows and compressible gas flows is used to predict the location and strength of oblique shocks in analogous tip leakage flows. Fea

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Pullan, Graham, John Denton, and Michael Dunkley. "An Experimental and Computational Study of the Formation of a Streamwise Shed Vortex in a Turbine Stage." Journal of Turbomachinery 125, no. 2 (2003): 291–97. http://dx.doi.org/10.1115/1.1545766.

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Shear layers shed by aircraft wings roll up into vortices. A similar, though far less common, phenomenon can occur in the wake of a turbomachine blade. This paper presents experimental data from a new single-stage turbine that has been commissioned at the Whittle Laboratory. Two low-aspect ratio stators have been tested with the same rotor row. Surface flow visualization illustrates the extremely strong secondary flows present in both NGV designs. These secondary flows lead to conventional passage vortices, but also to an intense vortex sheet which is shed from the trailing edge of the blades.

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Borges, J. E. "A Three-Dimensional Inverse Method for Turbomachinery: Part I—Theory." Journal of Turbomachinery 112, no. 3 (1990): 346–54. http://dx.doi.org/10.1115/1.2927666.

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There are surprisingly few inverse methods described in the literature that are truly three dimensional. Here, one such method is presented. This technique uses as input a prescribed distribution of the mean swirl, i.e., radius times mean tangential velocity, given throughout the meridional section of the machine. In the present implementation the flow is considered inviscid and incompressible and is assumed irrotational at the inlet to the blade row. In order to evaluate the velocity field inside the turbomachine, the blades (supposed infinitely thin) are replaced by sheets of vorticity, whos

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Zhao, Xiao-lu, Chun-lin Sun, and Chung-Hua Wu. "A Simple Method for Solving Three-Dimensional Inverse Problems of Turbomachine Flow and the Annular Constraint Condition." Journal of Engineering for Gas Turbines and Power 107, no. 2 (1985): 293–300. http://dx.doi.org/10.1115/1.3239714.

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In 1950, Wu [1] suggested that the three-dimensional inverse (design) problem of turbomachine flow may be solved approximately by a Taylor series expansion in the circumferential direction based on the known flow variation over an S2 stream surface in the midchannel of the blade passage. This idea has been realized recently. A new coordinate transformation has been developed. The coordinate surfaces are coincident with the S2 stream surfaces. This transformation leads to a new method to calculate the aerodynamic equations of three-dimensional flow. By the use of this transformation, a high-ord

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Sawyer, Scott D., and Sanford Fleeter. "Active Control of Discrete-Frequency Turbomachinery Noise Using a Rotary-Valve Actuator." Journal of Engineering for Gas Turbines and Power 122, no. 2 (2000): 226–32. http://dx.doi.org/10.1115/1.483199.

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Turbomachine discrete-frequency tones, a significant environmental concern, are generated by rotor-stator interactions. Specific spatial modes are generated, but not all generated modes propagate to the far field. It is the propagating spatial modes generated by rotor-stator interaction that represent the community-disturbing far field discrete-frequency noise. Fundamental active airfoil source discrete-frequency noise control experiments are performed, with the active airfoil source control optimized to generate propagating spatial modes to cancel the propagating spatial modes generated by th

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Liu, C. H., C. Zang, F. Li, and E. P. Petrov. "High Frequency Modal Testing of the Multiblade Packets Using a Noncontact Measurement and Excitation System." Shock and Vibration 2020 (February 27, 2020): 1–12. http://dx.doi.org/10.1155/2020/8740941.

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High cycle failure of blades and vanes caused by the vibration is one of the major causes reducing the lifetime of turbomachines. For multiblade packets, the failure may occur at vibrations with high frequencies that can reach up to tens of kHz. The experimental modal testing of blades is crucial for the validation of numerical models and for the optimization of turbomachine design. In this paper, the test rig and procedure for measurements of dynamic characteristics of lightweight multiblade packets in wide and high frequency ranges are developed. The measurements are based on a noncontact ex

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Dostal, Jan, and Jan Kuzel. "ANALYTICAL METHODS FOR CALCULATING FAN AERODYNAMICS." Acta Polytechnica 55, no. 6 (2015): 373. http://dx.doi.org/10.14311/ap.2015.55.0373.

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This paper presents results obtained between 2010 and 2014 in the field of fan aerodynamics at the Department of Composite Technology at the VZLÚ aerospace research and experimental institute in Prague – Letnany. The need for rapid and accurate methods for the preliminary design of blade machinery led to the creation of a mathematical model based on the basic laws of turbomachine aerodynamics. The mathematical model, the derivation of which is briefly described below, has been encoded in a computer programme, which enables the theoretical characteristics of a fan of the designed geometry to be

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Langston, Lee S. "Fitting a Pitch." Mechanical Engineering 131, no. 12 (2009): 38–42. http://dx.doi.org/10.1115/1.2009-dec-4.

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This article discusses gas turbine efficiency, which is an essential but often unappreciated aspect of turbomachine design pitch. To an engineer, the pitch of a turbo machinery blade is the angle at a representative blade cross-section between the blade chord line and the plane of the blade’s rotation. An axial flow gas turbine consists of many rows of rotating blades, interspersed with rows of stationary airfoils, called vanes or stators. The gas turbine compressor (whose first row of rotating blades in a jet engine may be a fan) draws in air, which after passing through a combustor to add en

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Nejad, J., A. Riasi, and A. Nourbakhsh. "Efficiency improvement of regenerative pump using blade profile modification: Experimental study." Proceedings of the Institution of Mechanical Engineers, Part E: Journal of Process Mechanical Engineering 233, no. 3 (2018): 448–55. http://dx.doi.org/10.1177/0954408918763554.

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Regenerative flow pump is a kind of turbomachine with the ability to generate high heads at relatively low flow rates. Despite having low hydraulic efficiency, regenerative pumps have found many applications in industries due to their simplicity, compact size, low manufacturing costs, and low specific speed. In this paper, an experimental study has been carried out to investigate the influence of impeller blade change on the performance of regenerative pump. To this end, the straight radial blades were changed to curved blades with the same inlet/outlet angles. Three forward curved blade impel

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Goodisman, M. I., M. L. G. Oldfield, R. C. Kingcombe, T. V. Jones, R. W. Ainsworth, and A. J. Brooks. "An Axial Turbobrake." Journal of Turbomachinery 114, no. 2 (1992): 419–25. http://dx.doi.org/10.1115/1.2929160.

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The “Axial Turbobrake” (patent applied for) is a novel turbomachine that can be used to absorb power generated by test turbines. Unlike a compressor, there is no pressure recovery through the turbobrake. This simplifies the aerodynamic design and enables high-stage loadings to be achieved. The blades used have high-turning two-dimensional profiles. This paper describes a single-stage axial turbobrake, which is driven by the exhaust gas of the test turbine and is isolated from the turbine by a choked throat. In this configuration no fast-acting controls are necessary as the turbobrake operates

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43

Uzol, Oguz, Yi-Chih Chow, Joseph Katz, and Charles Meneveau. "Average Passage Flow Field and Deterministic Stresses in the Tip and Hub Regions of a Multistage Turbomachine." Journal of Turbomachinery 125, no. 4 (2003): 714–25. http://dx.doi.org/10.1115/1.1625692.

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This paper continues our effort to study the dynamics of deterministic stresses in a multistage turbomachine using experimental data. Here we focus on the tip and hub regions and compare them to midspan data obtained in previous studies. The analysis is based on data obtained in particle image velocimetry (PIV) measurements performed in the second stage of a two-stage turbomachine. A complete data set is obtained using blades and fluid with matched optical index of refraction. Previous measurements at midspan have shown that at midspan and close to design conditions, the deterministic kinetic

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Smout, P. D., and P. C. Ivey. "Investigation of Wedge Probe Wall Proximity Effects: Part 1—Experimental Study." Journal of Engineering for Gas Turbines and Power 119, no. 3 (1997): 598–604. http://dx.doi.org/10.1115/1.2817026.

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Conventional three-hole wedge probes fail to measure the correct static pressure when operating in close proximity to a wall or boundary through which the probe is inserted. The free-stream pressure near the outer wall of a turbomachine may be overindicated by up to 20 percent dynamic head. This paper reports a series of experiments aimed at quantifying this so-called “wall proximity effect.” It is shown from a factorial experiment that probe wedge angle, stem design, and free-stream Mach number all have a significant influence. The yaw angle sensitivity of wedge probes is also found to depend

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45

Tangredi, Anna, Enrico Meli, Andrea Rindi, et al. "Development and Experimental Validation of Auxiliary Rolling Bearing Models for Active Magnetic Bearings (AMBs) Applications." International Journal of Rotating Machinery 2019 (April 1, 2019): 1–19. http://dx.doi.org/10.1155/2019/4675286.

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Nowadays, the search for increasing performances in turbomachinery applications has led to a growing utilization of active magnetic bearings (AMBs), which can bring a series of advantages thanks to their features: AMBs allow the machine components to reach higher peripheral speeds; in fact there are no wear and lubrication problems as the contact between bearing surfaces is absent. Furthermore, AMBs characteristic parameters can be controlled via software, optimizing machine dynamics performances. However, active magnetic bearings present some peculiarities, as they have lower load capacity th

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Picard, Benoit, Mathieu Picard, Jean-Sébastien Plante, and David Rancourt. "Optimum sub-megawatt electric-hybrid power source selection." Aircraft Engineering and Aerospace Technology 92, no. 5 (2020): 717–26. http://dx.doi.org/10.1108/aeat-06-2019-0119.

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Purpose The limited energy density of batteries generates the need for high-performance power sources for emerging eVTOL applications with radical operational improvement potential over traditional aircraft. This paper aims to evaluate on-design and off-design recuperated turbogenerator performances based on newly developed compression loaded ceramic turbines, the Inside-out Ceramic Turbine (ICT), in order to select the optimum engine configuration for sub-megawatt systems. Design/methodology/approach System-level thermal engine modeling is combined with electric generators and power electroni

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Nejadrajabali, J., A. Riasi, and S. A. Nourbakhsh. "Flow Pattern Analysis and Performance Improvement of Regenerative Flow Pump Using Blade Geometry Modification." International Journal of Rotating Machinery 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/8628467.

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Regenerative pump is a low specific speed and rotor-dynamic turbomachine capable of developing high heads at low flow rates. In this paper, a numerical study has been carried out in order to investigate the effect of blade angle on the performance of a regenerative pump. Two groups of impellers were employed. The first type has symmetric angle blades with identical inlet/outlet angles of ±10°, ±30°, and ±50° and the second group has nonsymmetric angle blades in which the inlet angle was set to 0° and six different angles of ±10°, ±30°, and ±50° were designed for the outlet of the blades. A tot

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Nejad, Jafar, Alireza Riasi, and Ahmad Nourbakhsh. "Parametric study and performance improvement of regenerative flow pump considering the modification in blade and casing geometry." International Journal of Numerical Methods for Heat & Fluid Flow 27, no. 8 (2017): 1887–906. http://dx.doi.org/10.1108/hff-03-2016-0088.

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Purpose Regenerative flow pump (RFP) is a rotodynamic turbomachine capable of developing high pressure rise at low flow rates. This paper aims to numerically investigate the performance of a regenerative pump considering the modification in blade and casing geometry. Design/methodology/approach The radial blade shape was changed to the bucket form and a core is added to flow path. A parametric study was performed to improve the performance of the pump. Thus, the effect of change in blade angle, chord, height, pitch to chord ratio and also inlet port on the performance of RFP was investigated.

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Mignolet, M. P., A. J. Rivas-Guerra, and J. P. Delor. "Identification of Mistuning Characteristics of Bladed Disks From Free Response Data—Part I." Journal of Engineering for Gas Turbines and Power 123, no. 2 (1999): 395–403. http://dx.doi.org/10.1115/1.1338949.

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The focus of the present two-part investigation is on the estimation of the dynamic properties, i.e., masses, stiffnesses, natural frequencies, mode shapes and their statistical distributions, of turbomachine blades to be used in the accurate prediction of the forced response of mistuned bladed disks. As input to this process, it is assumed that the lowest natural frequencies of the blades alone have been experimentally measured, for example, in a broach block test. Since the number of measurements is always less than the number of unknowns, this problem is indeterminate in nature. In this fir

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Agromayor, Roberto, Bernhard Müller, and Lars O. Nord. "One-Dimensional Annular Diffuser Model for Preliminary Turbomachinery Design." International Journal of Turbomachinery, Propulsion and Power 4, no. 3 (2019): 31. http://dx.doi.org/10.3390/ijtpp4030031.

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Annular diffusers are frequently used in turbomachinery applications to recover the discharge kinetic energy and increase the total-to-static isentropic efficiency. Despite its strong influence on turbomachinery performance, the diffuser is often neglected during the preliminary design. In this context, a one-dimensional flow model for annular diffusers that accounts for the impact of this component on turbomachinery performance was developed. The model allows use of arbitrary equations of state and to account for the effects of area change, heat transfer, and friction. The mathematical proble

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