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Journal articles on the topic 'Turbomachinery'

Author: Grafiati

Published: 4 June 2021

Last updated: 3 May 2025

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1

Sazonov, Yuri A., Mikhail A. Mokhov, Inna V. Gryaznova, Victoria V. Voronova, Khoren A. Tumanyan, Mikhail A. Frankov, and Nikolay N. Balaka. "Simulation of Hybrid Mesh Turbomachinery using CFD and Additive Technologies." Civil Engineering Journal 8, no. 12 (December 1, 2022): 3815–30. http://dx.doi.org/10.28991/cej-2022-08-12-011.

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This paper develops schematics and evaluates the performance of hybrid mesh turbomachinery at the patenting stage of individual technical solutions. This type of turbomachine uses reduced-sized blades and also forms flow channels with a mesh structure between the blades. The research methods are based on simulations using computational fluid dynamics (CFD) and additive technologies. An intermediate conclusion is that a new scientific direction for investigating and creating hybrid mesh turbomachinery equipped with mesh jet control systems was formed to develop Euler's ideas. This paper describes new possibilities for the simultaneous implementation of two workflows in a single impeller: 1) Turbine workflow, and 2) Compressor workflow. Calculation methods showed possible improvements in the performance of the new turbomachines. This paper considers options for mesh turbomachine operation in the two-stage gas generator mode with partial involvement of atmospheric air in the workflow. Preliminary calculations based on examples show that it is possible to expect a two- to four-times increase in thrust when using hybrid mesh turbomachines. Ongoing studies mainly focus on developing multi-mode turbomachinery that works in complicated conditions, such as offshore oil and gas fields, but some research results are applicable in other industries, for example, in developing hybrid propulsion systems or propulsors. Doi: 10.28991/CEJ-2022-08-12-011 Full Text: PDF

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2

Bonalumi, Davide, Antonio Giuffrida, and Federico Sicali. "Thermo-economic analysis of a supercritical CO₂-based waste heat recovery system." E3S Web of Conferences 312 (2021): 08022. http://dx.doi.org/10.1051/e3sconf/202131208022.

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This work investigates the performance of a supercritical CO2 cycle as the bottoming cycle of a commercial gas turbine with 4.7 MW of electric power output. In detail, the partial heating cycle is the layout chosen for the interesting trade-off between heat recovery and cycle efficiency with a limited number of components. Single-stage radial turbomachines are selected according to the theory of similitude. In particular, the compressor is a troublesome turbomachine as it works near the critical point where significant variations of the CO2 properties occur. Efficiency values for turbomachinery are not fixed at first glance but result from actual size and running conditions, based on flow rates, enthalpy variations as well as rotational speeds. In addition, a limit is set for the machine Mach numbers in order to avoid heavily loaded turbomachinery. The thermodynamic study of the bottoming cycle is carried out by means of the mass and energy balance equations. A parametric analysis is carried out with particular attention to a number of specific parameters. Considering the power output calculated for the supercritical CO2 cycle, economic calculations are also carried out and the related costs compared to those specific of organic Rankine cycles with similar power output.

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3

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

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

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4

Stolarski, T. A. "Turbomachinery rotordynamics." Tribology International 28, no. 4 (June 1995): 262–63. http://dx.doi.org/10.1016/0301-679x(95)90034-p.

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5

Chupp, Raymond E., Robert C. Hendricks, Scott B. Lattime, and Bruce M. Steinetz. "Sealing in Turbomachinery." Journal of Propulsion and Power 22, no. 2 (March 2006): 313–49. http://dx.doi.org/10.2514/1.17778.

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6

Turton, R. K., and Jose A. Orozco. "Principles of Turbomachinery." Journal of Pressure Vessel Technology 108, no. 2 (May 1, 1986): 247. http://dx.doi.org/10.1115/1.3264781.

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7

Goodwin, M. J. "Rotordynamics of turbomachinery." Journal of Materials Processing Technology 21, no. 2 (March 1990): 239–40. http://dx.doi.org/10.1016/0924-0136(90)90010-r.

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8

Moreau, Stéphane, and Michel Roger. "Turbomachinery Noise Review." International Journal of Turbomachinery, Propulsion and Power 9, no. 1 (March 13, 2024): 11. http://dx.doi.org/10.3390/ijtpp9010011.

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The present paper is aimed at providing an updated review of prediction methods for the aerodynamic noise of ducted rotor–stator stages. Indeed, ducted rotating-blade technologies are in continuous evolution and are increasingly used for aeronautical propulsion units, power generation and air conditioning systems. Different needs are faced from the early design stage to the final definition of a machine. Fast-running, approximate analytical approaches and high-fidelity numerical simulations are considered the best-suited tools for each, respectively. Recent advances are discussed, with emphasis on their pros and cons.

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9

Xie, Rong, Muyan Chen, Weihuang Liu, Hongfei Jian, and Yanjun Shi. "Digital Twin Technologies for Turbomachinery in a Life Cycle Perspective: A Review." Sustainability 13, no. 5 (February 25, 2021): 2495. http://dx.doi.org/10.3390/su13052495.

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Turbomachinery from a life cycle perspective involves sustainability-oriented development activities such as design, production, and operation. Digital Twin is a technology with great potential for improving turbomachinery, which has a high volume of investment and a long lifespan. This study presents a general framework with different digital twin enabling technologies for the turbomachinery life cycle, including the design phase, experimental phase, manufacturing and assembly phase, operation and maintenance phase, and recycle phase. The existing digital twin and turbomachinery are briefly reviewed. New digital twin technologies are discussed, including modelling, simulation, sensors, Industrial Internet of Things, big data, and AI technologies. Finally, the major challenges and opportunities of DT for turbomachinery are discussed.

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10

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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11

RAHMATI, M. T. "APPLICATION OF A PRESSURE CORRECTION METHOD FOR MODELING INCOMPRESSIBLE FLOW THROUGH TURBOMACHINES." International Journal of Computational Methods 06, no. 03 (September 2009): 399–411. http://dx.doi.org/10.1142/s0219876209001905.

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This article presents the application of a RANS algorithm based on a pressure correction method for incompressible flow simulations of low-speed rotating machines. A numerical scheme is developed by extending a flow analysis in a stationary frame to a rotating frame for turbomachinery applications. The numerical scheme is explained with emphasis on the effect of rotation on the flow fields and turbulence modeling. The results of the numerical calculations for flow through an enclosed turbomachine and an extended turbomachine are compared with the experimental data to judge them on realistic flow patterns. The numerical solutions have shown reasonable agreement with the experimental data which demonstrates the merits and robustness of this numerical scheme.

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12

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

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

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13

Fujita, Hajime. "Aerodynamic Noise in Turbomachinery." Transactions of the Japan Society of Mechanical Engineers Series B 61, no. 591 (1995): 3804–10. http://dx.doi.org/10.1299/kikaib.61.3804.

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14

Srivastava, R., M. A. Bakhle, K. T.G., and G. L. Stefko. "Aeroelastic analysis of turbomachinery." International Journal of Numerical Methods for Heat & Fluid Flow 14, no. 3 (April 2004): 366–81. http://dx.doi.org/10.1108/09615530410518002.

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15

Srivastava, R., M. A. Bakhle, K. T.G., and D. Hoyniak. "Aeroelastic analysis of turbomachinery." International Journal of Numerical Methods for Heat & Fluid Flow 14, no. 3 (April 2004): 382–402. http://dx.doi.org/10.1108/09615530410518011.

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16

Sieverding, C. H. "Special Issue on Turbomachinery." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 6 (January 2005): i—ii. http://dx.doi.org/10.1177/095765090521900601.

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17

Scrivener, Colin, and Gerard Bois. "Special Issue on Turbomachinery." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 227, no. 6 (July 30, 2013): 627. http://dx.doi.org/10.1177/0957650913500183.

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18

Manna, Marcello. "Excellence in Turbomachinery Research: The Best of the 14th European Turbomachinery Conference." International Journal of Turbomachinery, Propulsion and Power 7, no. 3 (August 29, 2022): 25. http://dx.doi.org/10.3390/ijtpp7030025.

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19

Manna, Marcello. "Excellence in Turbomachinery Research: The Best of the 12th European Turbomachinery Conference." International Journal of Turbomachinery, Propulsion and Power 3, no. 3 (July 9, 2018): 19. http://dx.doi.org/10.3390/ijtpp3030019.

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20

De Choudhury, Pranabesh. "Application of Lund’s Stability Analysis Program in Design of Modern Turbomachinery." Journal of Vibration and Acoustics 125, no. 4 (October 1, 2003): 471–76. http://dx.doi.org/10.1115/1.1605991.

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The analytical tool developed by Lund has aided in the design and manufacture of modern turbomachinery operating at relatively high speeds, under severe operating conditions, with high gas pressure, and gas density. The purpose of this paper is to show, by means of selected problems, as a practicing engineer in the design of high speed turbomachinery, how the methods developed by Lund aided in the design and problem diagnostics of such turbomachinery.

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21

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 (September 17, 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 problem is formulated as an implicit system of ordinary differential equations that can be solved when the Mach number in the meridional direction is different than one. The model was verified against a reference case to assess that: (1) the stagnation enthalpy is conserved and (2) the entropy computation is consistent and it was found that the error of the numerical solution was always smaller than the prescribed integration tolerance. In addition, the model was validated against experimental data from the literature, finding that deviation between the predicted and measured pressure recovery coefficients was less than 2% when the best-fit skin friction coefficient is used. Finally, a sensitivity analysis was performed to investigate the influence of several input parameters on diffuser performance, concluding that: (1) the area ratio is not a suitable optimization variable because the pressure recovery coefficient increases asymptotically when this variable tends to infinity, (2) the diffuser should be designed with a positive mean wall cant angle to recover the tangential fraction of kinetic energy, (3) the mean wall cant angle is a critical design variable when the maximum axial length of the diffuser is constrained, and (4) the performance of the diffuser declines when the outlet hub-to-tip ratio of axial turbomachines is increased because the channel height is reduced.

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22

Wilcock, R. C., J. B. Young, and J. H. Horlock. "The Effect of Turbine Blade Cooling on the Cycle Efficiency of Gas Turbine Power Cycles." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 109–20. http://dx.doi.org/10.1115/1.1805549.

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A thermodynamic cycle analysis computer code for the performance prediction of cooled gas turbines has been used to calculate the efficiency of plants with varying combustor outlet temperature, compressor pressure ratio, and turbomachinery polytropic efficiency. It is shown that the polytropic efficiency exerts a major influence on the optimum operating point of cooled gas turbines: for moderate turbomachinery efficiency the search for enhanced combustor outlet temperature is shown to be logical, but for high turbomachinery efficiency this is not necessarily so. The sensitivity of the cycle efficiency to variation in the parameters determining the cooling flow rates is also examined. While increases in allowable blade metal temperature and film cooling effectiveness are more beneficial than improvements in other parameters, neither is as important as increase in turbomachinery aerodynamic efficiency.

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23

Salvadori, Simone, Massimiliano Insinna, and Francesco Martelli. "Unsteady Flows and Component Interaction in Turbomachinery." International Journal of Turbomachinery, Propulsion and Power 9, no. 2 (April 5, 2024): 15. http://dx.doi.org/10.3390/ijtpp9020015.

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Unsteady component interaction represents a crucial topic in turbomachinery design and analysis. Combustor/turbine interaction is one of the most widely studied topics both using experimental and numerical methods due to the risk of failure of high-pressure turbine blades by unexpected deviation of hot flow trajectory and local heat transfer characteristics. Compressor/combustor interaction is also of interest since it has been demonstrated that, under certain conditions, a non-uniform flow field feeds the primary zone of the combustor where the high-pressure compressor blade passing frequency can be clearly individuated. At the integral scale, the relative motion between vanes and blades in compressor and turbine stages governs the aerothermal performance of the gas turbine, especially in the presence of shocks. At the inertial scale, high turbulence levels generated in the combustion chamber govern wall heat transfer in the high-pressure turbine stage, and wakes generated by low-pressure turbine vanes interact with separation bubbles at low-Reynolds conditions by suppressing them. The necessity to correctly analyze these phenomena obliges the scientific community, the industry, and public funding bodies to cooperate and continuously build new test rigs equipped with highly accurate instrumentation to account for real machine effects. In computational fluid dynamics, researchers developed fast and reliable methods to analyze unsteady blade-row interaction in the case of uneven blade count conditions as well as component interaction by using different closures for turbulence in each domain using high-performance computing. This research effort results in countless publications that contribute to unveiling the actual behavior of turbomachinery flow. However, the great number of publications also results in fragmented information that risks being useless in a practical situation. Therefore, it is useful to collect the most relevant outcomes and derive general conclusions that may help the design of next-gen turbomachines. In fact, the necessity to meet the emission limits defined by the Paris agreement in 2015 obliges the turbomachinery community to consider revolutionary cycles in which component interaction plays a crucial role. In the present paper, the authors try to summarize almost 40 years of experimental and numerical research in the component interaction field, aiming at both providing a comprehensive overview and defining the most relevant conclusions obtained in this demanding research field.

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24

McNally, William D., and Peter M. Sockol. "Review—Computational Methods for Internal Flows With Emphasis on Turbomachinery." Journal of Fluids Engineering 107, no. 1 (March 1, 1985): 6–22. http://dx.doi.org/10.1115/1.3242443.

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A review is given of current computational methods for analyzing flows in turbomachinery and other related internal propulsion components. The methods are divided primarily into two classes, inviscid and viscous. The inviscid methods deal specifically with turbomachinery applications. Viscous methods, on the other hand, due to the state-of-the-art, deal with generalized duct flows as well as flows in turbomachinery passages. Inviscid methods are categorized into the potential, stream function, and Euler approaches. Viscous methods are treated in terms of parabolic, partially parabolic, and elliptic procedures.

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25

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

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

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26

Kim, Dokyu, Yongju Jeong, In Woo Son, and Jeong Ik Lee. "A New Windage Loss Model for S-CO2 Turbomachinery Design." Applied Sciences 13, no. 13 (June 24, 2023): 7463. http://dx.doi.org/10.3390/app13137463.

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A supercritical CO2 (S-CO2) Brayton cycle is a compact and simple power conversion system with competitive efficiency. However, the strong real gas effects of S-CO2 pose challenges to the design of a cycle and its components. In particular, designing turbomachinery for expansion and compression processes has to accurately reflect real gas effects. Windage loss is one of the major losses that affects the motor load and heat generation in turbomachinery. The windage loss has a substantial impact on the overall turbomachinery efficiency especially in an S-CO2 power cycle since the windage loss is reported to be the dominant loss mechanism due to high fluid density and high rotational speed. Therefore, an accurate windage loss model reflecting the real gas effect of S-CO2 is essential to obtaining an optimal design of turbomachinery as well as maximizing the performance of an S-CO2 power cycle. In this study, existing windage loss models are first compared to the recently obtained data from S-CO2 windage loss experiments conducted by the KAIST research team under S-CO2 conditions in order to understand the turbomachinery performance uncertainty caused by the windage loss models. This is followed by proposing a new windage model which explains data better.

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27

FUNAZAKI, Ken-ichi. "Unsteady Flow Phenomena in Turbomachinery." Proceedings of Mechanical Engineering Congress, Japan 2020 (2020): K05200. http://dx.doi.org/10.1299/jsmemecj.2020.k05200.

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28

Moinier, Pierre, and Michael B. Giles. "Eigenmode Analysis for Turbomachinery Applications." Journal of Propulsion and Power 21, no. 6 (November 2005): 973–78. http://dx.doi.org/10.2514/1.11000.

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29

De Jesus Rivera, Edward, Darrell Robinette, Jason Blough, Carl Anderson, Steve Frait, and Ram Sudarsan. "Mathematics of Turbomachinery: Centrifugal Impeller." SAE International Journal of Engines 13, no. 3 (June 24, 2020): 423–38. http://dx.doi.org/10.4271/03-13-03-0028.

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Burguburu, Ste´phane, Clement Toussaint, Christophe Bonhomme, and Gilles Leroy. "Numerical Optimization of Turbomachinery Bladings." Journal of Turbomachinery 126, no. 1 (January 1, 2004): 91–100. http://dx.doi.org/10.1115/1.1645869.

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An optimization process is used to design bladings in turbomachinery. A gradient-based method is coupled to Navier-Stokes solvers and is applied to three different bladings. A new rotor blade of a transonic compressor is designed by using a quasi three-dimensional approach, with a significant efficiency improvement at the design point. The off-design behavior of this new compressor is also checked afterwards. The same quasi three-dimensional approach is used on a stator blade of a turbine, but the whole stage is computed in this case. The losses are locally reduced, proving the good sensitivity of the solver. Finally, a new three-dimensional rotor blade of a compressor is designed by applying deformation functions on the initial shape. The efficiency is improved over a wide range of mass flow. The whole results indicate that the optimization process can find improved design and can be integrated in a design procedure.

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31

SUGIMURA, Kazuyuki. "Aerodynamic Shape Optimization of Turbomachinery." Journal of the Society of Mechanical Engineers 109, no. 1050 (2006): 403–4. http://dx.doi.org/10.1299/jsmemag.109.1050_403.

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32

Hamed, A., W. C. Tabakoff, and R. V. Wenglarz. "Erosion and Deposition in Turbomachinery." Journal of Propulsion and Power 22, no. 2 (March 2006): 350–60. http://dx.doi.org/10.2514/1.18462.

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33

Nishi, Michihiro, Shimpei Mizuki, and Hiroshi Tsukamoto. "Unsteday Flow Phenomena in Turbomachinery." Transactions of the Japan Society of Mechanical Engineers Series B 61, no. 591 (1995): 3811–16. http://dx.doi.org/10.1299/kikaib.61.3811.

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34

Campos, Emilio. "Ceas “Turbomachinery Broadband Noise Workshop”." International Journal of Aeroacoustics 9, no. 3 (May 2010): i—ii. http://dx.doi.org/10.1260/1475-472x.9.3.i.

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35

Peake, Nigel, and Anthony B. Parry. "Modern Challenges Facing Turbomachinery Aeroacoustics." Annual Review of Fluid Mechanics 44, no. 1 (January 21, 2012): 227–48. http://dx.doi.org/10.1146/annurev-fluid-120710-101231.

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36

He, L. "Fourier methods for turbomachinery applications." Progress in Aerospace Sciences 46, no. 8 (November 2010): 329–41. http://dx.doi.org/10.1016/j.paerosci.2010.04.001.

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37

Tucker, P. G. "Trends in turbomachinery turbulence treatments." Progress in Aerospace Sciences 63 (November 2013): 1–32. http://dx.doi.org/10.1016/j.paerosci.2013.06.001.

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38

Liu, Baojie, Xianjun Yu, Huoxing Liu, Haokang Jiang, Huijing Yuan, and Yueting Xu. "Application of SPIV in turbomachinery." Experiments in Fluids 40, no. 4 (January 24, 2006): 621–42. http://dx.doi.org/10.1007/s00348-005-0102-9.

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39

Beauchamp, Philip Paul, and A. Richard Seebass. "Shock-free turbomachinery blade design." AIAA Journal 23, no. 2 (February 1985): 249–53. http://dx.doi.org/10.2514/3.8902.

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40

Panwalker, A. S., A. Rajamani, and V. Ramamurti. "Turbomachinery Blade Dynamics -- a Review." Shock and Vibration Digest 22, no. 12 (December 1, 1990): 3–9. http://dx.doi.org/10.1177/058310249002201203.

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41

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

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Schorr, M., B. Valdez, A. So, and J. Flores. "Erosion-Corrosion in Industrial Turbomachinery." Materials Performance 51, no. 2 (February 1, 2012): 46–50. https://doi.org/10.5006/mp2012_51_2-46.

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Erosion-corrosion (EC) reduces the service life of turbomachines handling slurries. EC is a particular type of corrosion caused by the interaction of mechanical, hydrodynamic, chemical, and electrochemical processes acting on the surface of the equipment in various industries, including mineral, chemical, energy, and water. EC measuring devices that simulate the shear and impact forces encountered in industrial environments are applied and the results are presented.

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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 (May 28, 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 prior to heat exchange could be completed by small expanders to produce mechanical work, reducing exergy destruction and improving site-wide energy efficiency compared to throttling valves. Cost estimates for such machines are presented, which serve as a basis for case-specific investment calculations. The resulting payback times of less than 18 months highlight the economic potential such solutions.

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Korakianitis, T., J. I. Hochstein, and D. Zou. "Prediction of the Transient Thermodynamic Response of a Closed-Cycle Regenerative Gas Turbine." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 57–64. http://dx.doi.org/10.1115/1.1806449.

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Instantaneous-response and transient-flow component models for the prediction of the transient response of gas turbine cycles are presented. The component models are based on applications of the principles of conservation of mass, energy, and momentum. The models are coupled to simulate the system transient thermodynamic behavior, and used to predict the transient response of a closed-cycle regenerative Brayton cycle. Various system transients are simulated using: the instantaneous-response turbomachinery models coupled with transient-flow heat-exchanger models; and transient-flow turbomachinery models coupled with transient-flow heat-exchanger models. The component sizes are comparable to those for a solar-powered Space Station (radial turbomachinery), but the models can easily be expanded to other applications with axial turbomachinery. An iterative scheme based on the principle of conservation of working-fluid mass in the system is used to compute the mass-flow rate at the solar-receiver inlet during the transients. In the process the mass-flow rate of every component at every time step is also computed. Representative results of different system models are compared and discussed.

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Bogdanovic-Jovanovic, Jasmina, Bozidar Bogdanovic, and Dragica Milenkovic. "Determination of averaged axisymmetric flow surfaces according to results obtained by numerical simulation of flow in turbomachinery." Thermal Science 16, suppl. 2 (2012): 577–91. http://dx.doi.org/10.2298/tsci120426193b.

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In the increasing need for energy saving worldwide, the designing process of turbomachinery, as an essential part of thermal and hydroenergy systems, goes in the direction of enlarging efficiency. Therefore, the optimization of turbomachinery designing strongly affects the energy efficiency of the entire system. In the designing process of turbomachinery blade profiling, the model of axisymmetric fluid flows is commonly used in technical practice, even though this model suits only the profile cascades with infinite number of infinitely thin blades. The actual flow in turbomachinery profile cascades is not axisymmetric, and it can be fictively derived into the axisymmetric flow by averaging flow parameters in the blade passages according to the circular coordinate. Using numerical simulations of flow in turbomachinery runners, its operating parameters can be preliminarily determined. Furthermore, using the numerically obtained flow parameters in the blade passages, averaged axisymmetric flow surfaces in blade profile cascades can also be determined. The method of determination of averaged flow parameters and averaged meridian streamlines is presented in this paper, using the integral continuity equation for averaged flow parameters. With thus obtained results, every designer can be able to compare the obtained averaged flow surfaces with axisymmetric flow surfaces, as well as the specific work of elementary stages, which are used in the procedure of blade designing. Numerical simulations of flow in an exemplary axial flow pump, used as a part of the thermal power plant cooling system, were performed using Ansys CFX.

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Rossikhin, Anton A. "Frequency-domain method for multistage turbomachine tone noise calculation." International Journal of Aeroacoustics 16, no. 6 (September 2017): 491–506. http://dx.doi.org/10.1177/1475472x17730458.

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A method of frequency-domain calculation of the multistage turbomachinery tone noise is presented. The method is based on the kinematic relations featuring dependence of flow fields in a turbomachine on time and circumferential angle. It solves the flow in several blade passages inside each row and can be used in conjunction with nonlinear equations. The method is developed at Central Institute of Aviation Motor and implemented in the Three Dimensional Acoustics Solver in-house solver. The multi-passage method is verified on two numerical problems. One is the tone noise generation by a 2D two stage turbine. The other is the problem of nonlinear interaction of circumferential modes in a 2D cylindrical channel.

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Abdelrhman, Ahmed M., Lim Meng Hee, M. S. Leong, and Salah Al-Obaidi. "Condition Monitoring of Blade in Turbomachinery: A Review." Advances in Mechanical Engineering 6 (January 1, 2014): 210717. http://dx.doi.org/10.1155/2014/210717.

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Blade faults and blade failures are ranked among the most frequent causes of failures in turbomachinery. This paper provides a review on the condition monitoring techniques and the most suitable signal analysis methods to detect and diagnose the health condition of blades in turbomachinery. In this paper, blade faults are categorised into five types in accordance with their nature and characteristics, namely, blade rubbing, blade fatigue failure, blade deformations (twisting, creeping, corrosion, and erosion), blade fouling, and loose blade. Reviews on characteristics and the specific diagnostic methods to detect each type of blade faults are also presented. This paper also aims to provide a reference in selecting the most suitable approaches to monitor the health condition of blades in turbomachinery.

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Lakshminarayana, B. "An Assessment of Computational Fluid Dynamic Techniques in the Analysis and Design of Turbomachinery—The 1990 Freeman Scholar Lecture." Journal of Fluids Engineering 113, no. 3 (September 1, 1991): 315–52. http://dx.doi.org/10.1115/1.2909503.

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The objective of this paper is to review and assess various computational fluid dynamic techniques used for the analysis and design of turbomachinery. Assessments of accuracy, efficiency, range of applicability, effect of physical approximations, and turbulence models are carried out. Suggestions are made as to the most appropriate technique to be used in a given situation. The emphasis of the paper is on the Euler and Navier-Stokes solvers with a brief assessment of boundary layer solutions, quasi three-dimensional and quasi-viscous techniques. A brief review of the techniques and assessment of the following methods are carried out: pressure-based method, explicit and implicit time marching techniques, pseudo-compressibility technique for incompressible flow, and zonal techniques. Recommendations are made with regard to the most appropriate technique for various flow regimes and types of turbomachinery, incompressible and compressible flows, cascades, rotors, stators, liquid-handling and gas-handling turbomachinery. Computational fluid dynamics has reached a high level of maturity; Euler codes are routinely used in design and analysis, and the Navier-Stokes codes will also be commonplace before the end of this decade. But to capture the realism in turbomachinery rotors and multi-stage turbomachinery, it is necessary to integrate the physical models along with the computational techniques. Turbulence and transition modeling, grid generation, and numerical techniques play a key role. Finally, recommendations are made for future research, including the need for validation data, improved acceleration schemes, techniques for two-phase flow, improved turbulence and transition models, development of zonal techniques, and grid generation techniques to handle complex geometries.

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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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Sandberg, Richard D., and Vittorio Michelassi. "Fluid Dynamics of Axial Turbomachinery: Blade- and Stage-Level Simulations and Models." Annual Review of Fluid Mechanics 54, no. 1 (January 5, 2022): 255–85. http://dx.doi.org/10.1146/annurev-fluid-031221-105530.

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The current generation of axial turbomachines is the culmination of decades of experience, and detailed understanding of the underlying flow physics has been a key factor for achieving high efficiency and reliability. Driven by advances in numerical methods and relentless growth in computing power, computational fluid dynamics has increasingly provided insights into the rich fluid dynamics involved and how it relates to loss generation. This article presents some of the complex flow phenomena occurring in bladed components of gas turbines and illustrates how simulations have contributed to their understanding and the challenges they pose for modeling. The interaction of key aerodynamic features with deterministic unsteadiness, caused by multiple blade rows, and stochastic unsteadiness, i.e., turbulence, is discussed. High-fidelity simulations of increasingly realistic configurations and models improved with help of machine learning promise to further grow turbomachinery performance and reliability and, thus, help fluid mechanics research have a greater industrial impact.

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