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Journal articles on the topic 'Turbomachinery flow'

Author: Grafiati

Published: 10 December 2022

Last updated: 31 July 2025

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1

Sazonov, Yuri A., Mikhail A. Mokhov, Inna V. Gryaznova, et al. "Simulation of Hybrid Mesh Turbomachinery using CFD and Additive Technologies." Civil Engineering Journal 8, no. 12 (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 describ

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2

Sazonov, Yuri Appolonievich, Mikhail A. Mokhov, Inna Vladimirovna Gryaznova, et al. "Designing Mesh Turbomachinery with the Development of Euler’s Ideas and Investigating Flow Distribution Characteristics." Civil Engineering Journal 8, no. 11 (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

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3

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 (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 experime

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4

RAHMATI, M. T. "APPLICATION OF A PRESSURE CORRECTION METHOD FOR MODELING INCOMPRESSIBLE FLOW THROUGH TURBOMACHINES." International Journal of Computational Methods 06, no. 03 (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 fl

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5

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 turbomachiner

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6

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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7

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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8

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 cas

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9

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 (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 turbomachine

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10

Martelli, F., and V. Michelassi. "Viscous flow calculations in turbomachinery channels." Journal de Physique III 3, no. 2 (1993): 237–53. http://dx.doi.org/10.1051/jp3:1993129.

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11

Dring, R. P., and H. D. Joslyn. "Through-Flow Modeling of Axial Turbomachinery." Journal of Engineering for Gas Turbines and Power 108, no. 2 (1986): 246–53. http://dx.doi.org/10.1115/1.3239895.

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Through-flow analysis, which is at the heart of the aerodynamic design of turbomachinery, requires as aerodynamic input a row-by-row description of the airfoil loss, deviation, and blockage. Loss and deviation have been investigated extensively in both cascades and rotating rigs as well as in numerous two- and three-dimensional analytical studies. Blockage, however, has received far less attention. As defined herein, blockage is a measure of the departure of the flow field from the condition of axisymmetry which is assumed in the through-flow analysis. The full-span blockage distributions calc

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12

INOUE, Masahiro, and Masato FURUKAWA. "Measurements of Flow Field in Turbomachinery." Journal of the Society of Mechanical Engineers 89, no. 814 (1986): 1020–26. http://dx.doi.org/10.1299/jsmemag.89.814_1020.

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13

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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14

Adamczyk, John J. "Aerodynamic Analysis of Multistage Turbomachinery Flows in Support of Aerodynamic Design." Journal of Turbomachinery 122, no. 2 (1999): 189–217. http://dx.doi.org/10.1115/1.555439.

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This paper summarizes the state of 3D CFD based models of the time-averaged flow field within axial flow multistage turbomachines. Emphasis is placed on models that are compatible with the industrial design environment and those models that offer the potential of providing credible results at both design and off-design operating conditions. The need to develop models free of aerodynamic input from semiempirical design systems is stressed. The accuracy of such models is shown to be dependent upon their ability to account for the unsteady flow environment in multistage turbomachinery. The releva

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15

Wadia, A. R., and B. F. Beacher. "Three-Dimensional Relief in Turbomachinery Blading." Journal of Turbomachinery 112, no. 4 (1990): 587–96. http://dx.doi.org/10.1115/1.2927697.

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The leading edge region of turbomachinery blading in the vicinity of the endwalls is typically characterized by an abrupt increase in the inlet flow angle and a reduction in total pressure associated with endwall boundary layer flow. Conventional two-dimensional cascade analysis of the airfoil sections at the endwalls indicates large leading edge loadings, which are apparently detrimental to the performance. However, experimental data exist that suggest that cascade leading edge loading conditions are not nearly as severe as those indicated by a two-dimensional cascade analysis. This discrepan

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16

Yang, Hyeonmo, Kyoung-Yong Lee, Youngseok Choi, and Kyungseok Jeong. "Visualization of Flow inside a Regenerative Turbomachinery." International Journal of Fluid Machinery and Systems 7, no. 2 (2014): 80–85. http://dx.doi.org/10.5293/ijfms.2014.7.2.080.

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17

Lenherr, Christian, Martin Oschwald, Anestis I. Kalfas, and Reza S. Abhari. "Flow adaptive aerodynamic probe for turbomachinery flows." E3S Web of Conferences 345 (2022): 01007. http://dx.doi.org/10.1051/e3sconf/202234501007.

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In order to enable turbomachinery research to obtain data highly resolved in space and time, a novel flow adaptive aerodynamic probe concept has been developed and presented in this paper. The algorithm selects the measurement positions of the probe automatically and therefore provides higher measurement fidelity compared to traditional methods. The development of the adaptive algorithm has been done in several steps. First an automatic 1Dtraversing algorithm has been developed. The following steps dealt with the subject of a 2D adaptive flow concept development, whereas primarily visual progr

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18

HAYAMI, Hiroshi. "Flow in Turbomachinery and Application of PIV." Proceedings of the Fluids engineering conference 2004 (2004): 3. http://dx.doi.org/10.1299/jsmefed.2004.3.

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19

Schafer, O. "Simulation of unsteady compressible flow in turbomachinery." Progress in Computational Fluid Dynamics, An International Journal 2, no. 1 (2002): 1. http://dx.doi.org/10.1504/pcfd.2002.003212.

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20

Choi, Jong-Soo. "Discharge flow measurements of a centrifugal turbomachinery." KSME Journal 8, no. 2 (1994): 152–60. http://dx.doi.org/10.1007/bf02953264.

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21

Zhou, Xin, Zhitao Zuo, Qi Liang, Hucan Hou, Hongtao Tang, and Haisheng Chen. "Synergy Methodology for Internal Flow of Turbomachinery." Journal of Thermal Science 29, no. 3 (2019): 730–42. http://dx.doi.org/10.1007/s11630-019-1205-6.

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22

Song, Kang, Ben Zhao, Harold Sun, and Weilin Yi. "A physics-based zero-dimensional model for the mass flow rate of a turbocharger compressor with uniform/distorted inlet condition." International Journal of Engine Research 20, no. 6 (2018): 624–39. http://dx.doi.org/10.1177/1468087418773673.

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Turbocharger compressor, when fitted to a vehicle, usually operates with a curved inlet pipe which leads to distorted inlet flow field, hence deteriorating compressor flow capability. During the measurement of compressor performance, turbocharger-engine matching and controller design, the inlet flow field is, however, assumed to be uniform, which deviates from the real-world conditions. Consequently, the overall system performance could be compromised if the inlet distortion effect is ignored. To address this issue, in this article, a turbomachinery physics-based zero-dimensional model was pro

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23

Rossikhin, Anton A. "Frequency-domain method for multistage turbomachine tone noise calculation." International Journal of Aeroacoustics 16, no. 6 (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

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24

Salvadori, Simone, Massimiliano Insinna, and Francesco Martelli. "Unsteady Flows and Component Interaction in Turbomachinery." International Journal of Turbomachinery, Propulsion and Power 9, no. 2 (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

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25

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 (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

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26

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

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27

Chew, J. W. "Developments in turbomachinery internal air systems." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 223, no. 1 (2008): 189–234. http://dx.doi.org/10.1243/09544062jmes1140.

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Development of turbomachinery technology, including aircraft propulsion, has been an outstanding achievement of the last 50 years and, as illustrated by Ruffles in his paper ‘The future of aircraft propulsion’ (2000), further advances are expected in the future. Here, one particular aspect of turbomachinery technology, the internal air system is considered. An article by Dixon et al., published by the Institution of Mechanical Engineers in 2004, shows how computational modelling has become central to the design process and the importance of the internal air system in engine design. Bayley and

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28

Cinnella, P., P. De Palma, G. Pascazio, and M. Napolitano. "A Numerical Method for Turbomachinery Aeroelasticity." Journal of Turbomachinery 126, no. 2 (2004): 310–16. http://dx.doi.org/10.1115/1.1738122.

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This work provides an accurate and efficient numerical method for turbomachinery flutter. The unsteady Euler or Reynolds-averaged Navier-Stokes equations are solved in integral form, the blade passages being discretised using a background fixed C-grid and a body-fitted C-grid moving with the blade. In the overlapping region data are exchanged between the two grids at every time step, using bilinear interpolation. The method employs Roe’s second-order-accurate flux difference splitting scheme for the inviscid fluxes, a standard second-order discretisation of the viscous terms, and a three-level

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29

Farrell, K. J., and M. L. Billet. "A Correlation of Leakage Vortex Cavitation in Axial-Flow Pumps." Journal of Fluids Engineering 116, no. 3 (1994): 551–57. http://dx.doi.org/10.1115/1.2910312.

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Tip clearance flow in turbomachinery can lead to losses in efficiency and stall margin. In liquid handling turbomachinery, the vortical flow field, formed from the interaction of the leakage flow with the through-flow, is subject to cavitation. Furthermore, this flow field is complex and not well understood. A correlation of variables which predict the vortex minimum pressure has been formulated. Measurements of the important variables for this correlation have been made on a high Reynolds number (3 × 106) axial-flow test rig. The correlation has been applied to the measured data and other dat

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30

Adamczyk, J. J., R. A. Mulac, and M. L. Celestina. "A Model for Closing the Inviscid Form of the Average-Passage Equation System." Journal of Turbomachinery 108, no. 2 (1986): 180–86. http://dx.doi.org/10.1115/1.3262035.

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A mathematical model is proposed for closing or mathematically completing the system of equations which describes the time-averaged flow field through the blade passages of multistage turbomachinery. These equations, referred to as the average-passage equation system, govern a conceptual model which has proven useful in turbomachinery aerodynamic design and analysis. The closure model is developed so as to insure a consistency between these equations and the axisymmetric through-flow equations. The closure model was incorporated into a computer code for use in simulating the flow field about a

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31

He, L., and K. Sato. "Numerical Solution of Incompressible Unsteady Flows in Turbomachinery." Journal of Fluids Engineering 123, no. 3 (2000): 680–85. http://dx.doi.org/10.1115/1.1383595.

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A three-dimensional incompressible viscous flow solver of the thin-layer Navier-Stokes equations was developed for the unsteady turbomachinery flow computations. The solution algorithm for the unsteady flows combines the dual time stepping technique with the artificial compressibility approach for solving the incompressible unsteady flow governing equations. For time accurate calculations, subiterations are introduced by marching the equations in the pseudo-time to fully recover the incompressible continuity equation at each real time step, accelerated with a multi-grid technique. Computations

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32

Kämmerer, Steffen, Jürgen F. Mayer, Heinz Stetter, Meinhard Paffrath, Utz Wever, and Alexander R. Jung. "Development of a Three-Dimensional Geometry Optimization Method for Turbomachinery Applications." International Journal of Rotating Machinery 10, no. 5 (2004): 373–85. http://dx.doi.org/10.1155/s1023621x04000387.

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This article describes the development of a method for optimization of the geometry of three-dimensional turbine blades within a stage configuration. The method is based on flow simulations and gradient-based optimization techniques. This approach uses the fully parameterized blade geometry as variables for the optimization problem. Physical parameters such as stagger angle, stacking line, and chord length are part of the model. Constraints guarantee the requirements for cooling, casting, and machining of the blades.The fluid physics of the turbomachine and hence the objective function of the

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33

Cumpsty, N. A., and J. H. Horlock. "Averaging Nonuniform Flow for a Purpose." Journal of Turbomachinery 128, no. 1 (2005): 120–29. http://dx.doi.org/10.1115/1.2098807.

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Averaging nonuniform flow is important for the analysis of measurements in turbomachinery and gas turbines; more recently an important need for averaging arises with results of computational fluid dynamics (CFD). In this paper we show that there is a method for averaging which is “correct,” in the sense of preserving the essential features of the nonuniform flow, but that the type of averaging which is appropriate depends on the application considered. The crucial feature is the decision to retain or conserve those quantities which are most important in the case considered. Examples are given

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34

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 (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 the

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35

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 (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 ef

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Wissink, J. G., and W. Rodi. "Direct Numerical Simulations of Transitional Flow in Turbomachinery." Journal of Turbomachinery 128, no. 4 (2006): 668–78. http://dx.doi.org/10.1115/1.2218517.

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An overview is provided of various direct numerical simulations (DNS) of transitional flows in turbine-related geometries. Two flow cases are considered: the first case concerns separating flow over a flat plate and the second case flows in turbine cascades. In the first case, in which Re=60,000, either an oscillating oncoming flow (1) or a uniform flow with and without oncoming turbulent free-stream fluctuations (2) is prescribed at the inlet. In both subcases (1) and (2), separation is induced by a contoured upper wall. In (1), the separated boundary layer is found to roll up due to a Kelvin

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37

CHEN, Haisheng. "Review of investigation into internal flow of turbomachinery." Chinese Journal of Mechanical Engineering 43, no. 02 (2007): 1. http://dx.doi.org/10.3901/jme.2007.02.001.

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Lenherr, C., A. I. Kalfas, and R. S. Abhari. "A flow adaptive aerodynamic probe concept for turbomachinery." Measurement Science and Technology 18, no. 8 (2007): 2599–608. http://dx.doi.org/10.1088/0957-0233/18/8/035.

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39

Carstens, Volker, Ralf Kemme, and Stefan Schmitt. "Coupled simulation of flow-structure interaction in turbomachinery." Aerospace Science and Technology 7, no. 4 (2003): 298–306. http://dx.doi.org/10.1016/s1270-9638(03)00016-6.

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40

Madavan, N. K. "Unsteady turbomachinery flow simulations on massively parallel architectures." Computing Systems in Engineering 3, no. 1-4 (1992): 241–49. http://dx.doi.org/10.1016/0956-0521(92)90109-v.

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41

Basson, A., and B. Lakshminarayana. "Numerical Simulation of Tip Clearance Effects in Turbomachinery." Journal of Turbomachinery 117, no. 3 (1995): 348–59. http://dx.doi.org/10.1115/1.2835668.

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The numerical formulation developed here includes an efficient grid generation scheme, particularly suited to computational grids for the analysis of turbulent turbo-machinery flows and tip clearance flows, and a semi-implicit, pressure-based computational fluid dynamics scheme that directly includes artificial dissipation, and is applicable to both viscous and inviscid flows. The value of this artificial dissipation is optimized to achieve accuracy and convergency in the solution. The numerical model is used to investigate the structure of tip clearance flows in a turbine nozzle. The structur

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42

Sbardella, L., and M. Imregun. "Linearized Unsteady Viscous Turbomachinery Flows Using Hybrid Grids." Journal of Turbomachinery 123, no. 3 (2001): 568–82. http://dx.doi.org/10.1115/1.1371777.

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The paper describes the theory and the numerical implementation of a three-dimensional finite volume scheme for the solution of the linearized, unsteady Favre-averaged Navier–Stokes equations for turbomachinery applications. A further feature is the use of mixed element grids, consisting of triangles and quadrilaterals in two dimensions, and of tetrahedra, triangular prisms, and hexahedra in three dimensions. The linearized unsteady viscous flow equations are derived by assuming small harmonic perturbations from a steady-state flow and the resulting equations are solved using a pseudo-time mar

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Kirk, R. G., K. V. S. Raju, and K. Ramesh. "PC-Based Analysis of Turbomachinery Vibration." Shock and Vibration Digest 31, no. 6 (1999): 449–54. http://dx.doi.org/10.1177/058310249903100602.

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Vanaei, Hamid Reza, Sofiane Khelladi, Ivan Dobrev, et al. "Performance and Efficiency of Cross-Flow Fans—A Review." Energies 16, no. 23 (2023): 7798. http://dx.doi.org/10.3390/en16237798.

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Cross-Flow Fans (CFFs) have been widely applied in the automotive and domestic air conditioning industries in recent decades. They are high-pressure coefficient turbomachines compacted diametrically, and thus, the complex interactions of these fans require thorough evaluation. Their innovation has opened up new directions in turbomachinery, and both academic research and industry have seen numerous efforts to develop these types of fans. Despite extensive work, optimizing and improving their performance remains a challenge. Enhancing their efficiency necessitates improvements in structural cha

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Kupferschmied, Peter, Pascal Ko¨ppel, Christian Roduner, and Georg Gyarmathy. "On the Development and Application of the Fast-Response Aerodynamic Probe System in Turbomachines—Part 1: The Measurement System." Journal of Turbomachinery 122, no. 3 (1999): 505–16. http://dx.doi.org/10.1115/1.1303702.

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This contribution gives an overview of the current state, performance, and limitations of the fast-response aerodynamic probe measurement system developed at the Turbomachinery Lab of the ETH Zurich. In particular, the following topics are addressed: • Probe technology: Miniature probes with tip diameter ranging from 0.84 to 1.80 mm (one-sensor and three-sensor probes, respectively) have been developed. New technologies derived from microelectronics and micromechanics have been used to achieve an adequate packaging of the microsensor chips used. Both the sensor packaging and the sensor calibra

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Brodersen, S., and D. Wulff. "Measurements of the Pressure and Velocity Distribution in Low-Speed Turbomachinery by Means of High-Frequency Pressure Transducers." Journal of Turbomachinery 114, no. 1 (1992): 100–107. http://dx.doi.org/10.1115/1.2927972.

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The flow in a low-speed, single-state compressor with a very high blade loading has been measured using a two-probe arrangement. The measuring technique and data reduction procedure described have been especially adjusted for application in low-speed turbomachinery. Those machines show only small pressure fluctuations in the flow downstream of the rotor, for which specific requirements concerning the measuring technique have been taken into account. The probes used contain unsteady pressure transducers and simulate an unsteady multisensor pressure probe. This technique proves to be suitable fo

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Lee, C., and M. K. Chung. "Secondary flow loss and deviation models for through-flow analysis of axial flow turbomachinery." Mechanics Research Communications 18, no. 6 (1991): 403–8. http://dx.doi.org/10.1016/0093-6413(91)90053-y.

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Gossweiler, C. R., P. Kupferschmied, and G. Gyarmathy. "On Fast-Response Probes: Part 1—Technology, Calibration, and Application to Turbomachinery." Journal of Turbomachinery 117, no. 4 (1995): 611–17. http://dx.doi.org/10.1115/1.2836579.

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A system for fast-response probe measurements in turbomachine flows has been developed and tested. The system has been designed for 40 kHz bandwidth and used with various in-house built probes accommodating up to four piezoresistive pressure transducers. The present generation of probes works accurately up to several bar pressure and 120°C temperature. The probes were found to be quite robust. The use of a miniature pressure transducer placed in the head of a probe showed that a precise packaging technique and a careful compensation of errors can considerably improve the accuracy of the pressu

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Dring, R. P., and G. C. Oates. "Throughflow Theory for Nonaxisymmetric Turbomachinery Flow: Part I—Formulation." Journal of Turbomachinery 112, no. 3 (1990): 320–26. http://dx.doi.org/10.1115/1.2927661.

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Throughflow theory has been limited in its applicability and in its accuracy by the fact that it has not historically been cast in a form that can account for the non-axisymmetries that naturally arise in turbomachinery flow due to the presence of finite numbers of rotor and stator airfoils. The attempt to circumvent this limitation by the introduction of an aerodynamic blockage factor has been demonstrated in earlier work to produce fundamental inconsistencies in the calculation, which lead to significant errors in the regions of the flow where the nonaxisymmetries are severe. The formulation

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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 (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 captur

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