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Journal articles on the topic 'Radial flow compressors'

Author: Grafiati

Published: 6 September 2023

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1

Tan, J., X. Wang, D. Qi, and R. Wang. "The effects of radial inlet with splitters on the performance of variable inlet guide vanes in a centrifugal compressor stage." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 225, no. 9 (2011): 2089–105. http://dx.doi.org/10.1177/0954406211407799.

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Variable inlet guide vanes (VIGVs) can regulate pressure ratio and mass flow at constant rotational speed in centrifugal compressors as a result of inducing a controlled prewhirl in front of impellers. Radial inlets and VIGVs are typical upstream components in front of the first-stage impellers in many industrial centrifugal compressors. However, previous investigations on VIGVs in centrifugal compressors were mostly conducted under the condition of axial inlets, and this study aims to focus on the effects of radial inlet on the VIGVs performance of a centrifugal compressor stage. The axial in

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2

Bozza, F., A. Senatore, and R. Tuccillo. "Thermal Cycle Analysis and Component Aerodesign for Gas Turbine Concept in Low-Range Cogenerating Systems." Journal of Engineering for Gas Turbines and Power 118, no. 4 (1996): 792–802. http://dx.doi.org/10.1115/1.2816995.

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The authors link together their previous experiences in gas turbine plant analysis and aerodynamic design of radial flow compressors. In recent papers they have introduced a method for the performance estimation of gas turbine engines, based on the prediction of the matching conditions among the several components in the whole operating range. On the other hand they have expressly paid attention to the problem of optimal design of radial flow compressors for satisfactory operation within an assigned operating range. In this paper, the authors present an integrated method, which aims to define

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3

Berezin, A. V., A. F. Kuftov, and I. B. Shkurikhin. "Blading impellers of radial-flow compressors." Journal of Machinery Manufacture and Reliability 44, no. 7 (2015): 616–25. http://dx.doi.org/10.3103/s1052618815070055.

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4

Prata, A. T., J. R. S. Fernandes, and F. Fagotti. "PISTON LUBRICATION IN RECIPROCATING COMPRESSORS." Revista de Engenharia Térmica 1, no. 1 (2001): 56. http://dx.doi.org/10.5380/reterm.v1i1.3501.

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Piston dynamics plays a fundamental role in two critical processes related to fluid flow in reciprocating compressors. The first is the refrigerant leakage through the radial clearance, which may cause considerable loss in the pumping efficiency of the compressor. The second process is the viscous friction associated with the lubricant film in the radial clearance; certainly a significant factor in the compressor energy consumption. In the present contribution a numerical simulation of the piston movement inside the cylinder of a reciprocating compressor is performed. The compressor considered

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5

Eriksson, Lars-Erik. "Simulation of transonic flow in radial compressors." Computer Methods in Applied Mechanics and Engineering 64, no. 1-3 (1987): 95–111. http://dx.doi.org/10.1016/0045-7825(87)90035-1.

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6

Song, J. W., M. Raheel, and A. Engeda. "A compressible flow theory for regenerative compressors with aerofoil blades." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 217, no. 11 (2003): 1241–57. http://dx.doi.org/10.1243/095440603771665269.

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Regenerative flow compressors (RFCs) are rotodynamic machines capable of producing high heads at very low flowrates. They have very low specific speed and share some of the characteristics of positive displacement machines such as a roots blower, but without the problems of lubrication and wear. They can produce heads equivalent to that of several centrifugal stages from a single rotor with comparable tip speed. The compression process is usually not regarded as efficient. Typically they produce efficiency of less than 50 per cent but still they have found many applications because they allow

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7

Dutton, J. C., P. Piemsomboon, and P. E. Jenkins. "Flowfield and Performance Measurements in a Vaned Radial Diffuser." Journal of Fluids Engineering 108, no. 2 (1986): 141–47. http://dx.doi.org/10.1115/1.3242553.

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The flow characteristics of a vaned diffuser typical of those currently used in centrifugal compressors have been determined experimentally by using a static diffuser test rig. The vortex test vehicle (VTV) portion of this rig was used to simulate the essential features of the flow leaving the impeller of an actual compressor. The mean flow phenomena at the diffuser entrance and the static pressure recovery along the diffuser passage have been determined. In addition, the flow angle and Mach number distributions at several key locations throughout the diffuser channel have been obtained. The m

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8

Prata, A. T., J. R. S. Fernandes, and F. Fagotti. "Dynamic Analysis of Piston Secondary Motion for Small Reciprocating Compressors." Journal of Tribology 122, no. 4 (2000): 752–60. http://dx.doi.org/10.1115/1.1314603.

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Piston dynamics plays a fundamental role in two critical processes related to fluid flow in reciprocating compressors. The first is the gas leakage through the radial clearance, which may cause considerable loss in the pumping efficiency of the compressor. The second process is the viscous friction associated with the lubricant film in the radial clearance. In the present contribution a numerical simulation is performed for a ringless piston inside the cylinder of a reciprocating compressor, including both the axial and the radial piston motion. The compressor considered here is a small hermet

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9

Rodgers, C. "Impingement Starting and Power Boosting of Small Gas Turbines." Journal of Engineering for Gas Turbines and Power 107, no. 4 (1985): 821–27. http://dx.doi.org/10.1115/1.3239817.

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The technology of high-pressure air or hot-gas impingement from stationary shroud supplementary nozzles onto radial outflow compressors and radial inflow turbines to permit rapid gas turbine starting or power boosting is discussed. Data are presented on the equivalent turbine component performance for convergent/divergent shroud impingement nozzles, which reveal the sensitivity of nozzle velocity coefficient with Mach number and turbine efficiency with impingement nozzle admission arc. Compressor and turbine matching is addressed in the transient turbine start mode with the possibility of oper

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10

Han, Fenghui, Zhe Wang, Yijun Mao, Jiajian Tan, and Wenhua Li. "Flow Control of Radial Inlet Chamber and Downstream Effects on a Centrifugal Compressor Stage." Applied Sciences 11, no. 5 (2021): 2168. http://dx.doi.org/10.3390/app11052168.

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Radial inlet chambers are widely used in various multistage centrifugal compressors, although they induce extra flow loss and inlet distortions. In this paper, the detailed flow characteristics inside the radial inlet chamber of an industrial centrifugal compressor have been numerically investigated for flow control and performance improvement. First, the numerical results are validated against the experimental data, and flow conditions inside the inlet chambers with different structures are compared. They indicate that, in the non-guide vane scheme, sudden expansions, tangential flows and flo

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11

Sundström, Elias, Bernhard Semlitsch, and Mihai Mihăescu. "Acoustic signature of flow instabilities in radial compressors." Journal of Sound and Vibration 434 (November 2018): 221–36. http://dx.doi.org/10.1016/j.jsv.2018.07.040.

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12

Sato, T., J. M. Oh, and A. Engeda. "Experimental and Numerical Investigation of the Flow in a Vaneless Diffuser of a Centrifugal Compressor Stage. Part 1: Experimental Investigation." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 219, no. 10 (2005): 1053–59. http://dx.doi.org/10.1243/095440605x31904.

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The flow in a radial vaneless diffuser downstream of a centrifugal compressor is highly complex, as the flow is turbulent, unsteady, viscous, and three-dimensional. Depending on the initial state of the end-wall boundary layers and the diffuser length, the flow may become fully developed or may separate from one of the walls. Therefore, to improve the diffuser performance, it is important to understand the flow field in the diffuser in detail. As the diffuser width is generally very small for most radial stages and an adverse pressure gradient exists, secondary flows are generated, making the

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13

Han, Fenghui, Zhe Wang, Yijun Mao, Jiajian Tan, and Wenhua Li. "Experimental and numerical studies on the influence of inlet guide vanes of centrifugal compressor on the flow field characteristics of inlet chamber." Advances in Mechanical Engineering 12, no. 11 (2020): 168781402097490. http://dx.doi.org/10.1177/1687814020974909.

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Inlet chambers (IC) are the typical upstream component of centrifugal compressors, and inlet guide vanes in the IC have a great impact on its internal flow and aerodynamic loss, which will significantly influence the performance of the downstream compressor stages. In this paper, an experimental study was carried out on the flow characteristics inside a radial IC of an industrial centrifugal compressor, including five testing sections and 968 measuring points for two schemes with and without guide vanes. Detailed distributions of flow parameters on each section were obtained as well as the ove

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14

Gallimore, S. J., and N. A. Cumpsty. "Spanwise Mixing in Multistage Axial Flow Compressors: Part I—Experimental Investigation." Journal of Turbomachinery 108, no. 1 (1986): 2–9. http://dx.doi.org/10.1115/1.3262019.

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Spanwise mixing has been shown to be an essential feature of multistage compressor aerodynamics. The cause of spanwise mixing in multistage axial flow compressors has been investigated directly by using an ethylene tracer gas technique in two low-speed, four-stage machines. The results show that the dominant mechanism is that of turbulent type diffusion and not the radial convection of flow properties as has been previously suggested. The mixing was also found to be substantially uniform in magnitude all the way across the span with levels similar to those found in two-dimensional turbulent wa

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15

Ehrich, F. "Rotor Whirl Forces Induced by the Tip Clearance Effect in Axial Flow Compressors." Journal of Vibration and Acoustics 115, no. 4 (1993): 509–15. http://dx.doi.org/10.1115/1.2930379.

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It is now widely recognized that destabilizing forces, tending to generate forward rotor whirl, are generated in axial flow turbines as a result of the nonuniform torque induced by the nonuniform tip-clearance in a deflected rotor—the so called Thomas/Alford force (Thomas, 1958, and Alford, 1965). It is also recognized that there will be a similar effect in axial flow compressors, but qualitative considerations cannot definitively establish the magnitude or even the direction of the induced whirling forces—that is, if they will tend to forward or backward whirl. Applying a “parallel compressor

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16

Moukalled, F., N. Naim, and I. Lakkis. "Computer-Aided Analysis of Centrifugal Compressors." International Journal of Mechanical Engineering Education 22, no. 4 (1994): 245–58. http://dx.doi.org/10.1177/030641909402200402.

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This paper describes computer-aided analysis of centrifugal compressors (CAACC), a micro-computer-based, interactive, and menu-driven software package for use as an educational tool by mechanical engineering students studying radial flow compressors. CAACC is written in the Pascal computer language and runs on IBM PC, or compatible, computers. In addition to solving for any unknown variables, the graphical utilities of the package allow the user to display a diagrammatic sketch of the compressor and to draw velocity diagrams at several locations. Furthermore, the program allows the investigati

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17

Leylek, J. H., and D. C. Wisler. "Mixing in Axial-Flow Compressors: Conclusions Drawn From Three-Dimensional Navier–Stokes Analyses and Experiments." Journal of Turbomachinery 113, no. 2 (1991): 139–56. http://dx.doi.org/10.1115/1.2929069.

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Extensive numerical analyses and experiments have been conducted to understand mixing phenomena in multistage, axial-flow compressors. For the first time in the literature the following are documented: Detailed three-dimensional Navier–Stokes solutions, with high order turbulence modeling, are presented for flow through a compressor vane row at both design and off-design (increased) loading; comparison of these computations with detailed experimental data show excellent agreement at both loading levels; the results are then used to explain important aspects of mixing in compressors. The three-

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18

Ziegler, Kai U., Heinz E. Gallus, and Reinhard Niehuis. "A Study on Impeller-Diffuser Interaction—Part I: Influence on the Performance." Journal of Turbomachinery 125, no. 1 (2003): 173–82. http://dx.doi.org/10.1115/1.1516814.

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The interaction between impeller and diffuser is considered to have strong influence on the flow in centrifugal compressors. However, the knowledge about this influence is still not satisfying. This two-part paper presents an experimental investigation of the effect of impeller-diffuser interaction on the unsteady and the time averaged flow field configuration in impeller and diffuser and the performance of these components. The flat wedge vaned diffuser of the investigated compressor allows an independent adjustment of diffuser vane angle and radial gap between impeller exit and diffuser vane

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19

Zhao, Wenfeng, Qun Zheng, Bin Jiang, and Aqiang Lin. "A Passive Control Method of Hub Corner Stall in a 1.5-Stage Axial Compressor under Low-Speed Conditions." Energies 13, no. 11 (2020): 2691. http://dx.doi.org/10.3390/en13112691.

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Since the use of the compressor of a ship gas turbine is unavoidable at a low-speed operation, the flow field characteristics and stall mechanism at off-design speeds are important aspects for compressor designers. In this study, the first 1.5 stages of an eight-stage compressor are numerically simulated. The mechanism of compressor rotor instability at lower speeds is identified. The characteristic lines of compressors with various partial clearance are calculated at low speed (0.6 N). The flow field of the same outlet pressure (near stall point of the original compressor without clearance) i

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20

Motriuk, R. W., and D. P. Harvey. "Centrifugal Compressor Modifications and Their Effect on High-Frequency Pipe Wall Vibration." Journal of Pressure Vessel Technology 120, no. 3 (1998): 276–82. http://dx.doi.org/10.1115/1.2842058.

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High-frequency pulsation generated by centrifugal compressors, with pressure wavelengths much smaller than the attached pipe diameter, can cause fatigue failures of the compressor internals, impair compressor performance, and damage the attached compressor piping. There are numerous sources producing pulsation in centrifugal compressors. Some of them are discussed in literature at large (Japikse, 1995; Niese, 1976). NGTL has experienced extreme high-frequency discharge pulsation and pipe wall vibration on many of its radial inlet high-flow centrifugal gas compressor facilities. These pulsation

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21

Li, Xiaoran, Weifeng Wu, Jing Zhang, Chengqiang Guo, Feng Ke, and Fuqiang Jiang. "Analysis of 3D Transient Flow in a High-Speed Scroll Refrigeration Compressor." Energies 16, no. 7 (2023): 3089. http://dx.doi.org/10.3390/en16073089.

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In mobile devices such as aircraft and electric vehicles, due to limited space, there are strict requirements on the volume and weight of the compressor mounted on the vehicle. Therefore, high-speed scroll compressors have attracted more and more attention because of their small size and light weight. In this paper, the numerical calculations and analysis of the three-dimensional (3D) transient flows in a high-speed scroll refrigeration compressor were established and validated. Circumferential gas intake was used in the simulation. According to the actual compressor size, the mesh generation

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22

Carsten, Degendorfer, Reza S. Abhari, Klemens Vogel, and René Hunziker. "Experimental and numerical investigation of blade resonance in a centrifugal compressor for varying gas properties." Journal of the Global Power and Propulsion Society 2 (September 20, 2018): Q15CRP. http://dx.doi.org/10.22261/jgpps.q15crp.

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The blades of centrifugal compressors are exposed to unsteady forces during operation which can result in resonance response conditions and failures due to high cycle fatigue. A typical source of excitation is the unsteady fluid structure interaction between the impeller blades and the downstream vaned diffuser. Centrifugal compressors are operated with various working fluids with a wide range of applications in the power and process industry. Understanding the excitation mechanisms for different working fluids will help to design aerodynamically efficient compressors, while ensuring mechanica

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23

Rakhmanina, L. A., A. V. Zuev, A. Yu Petrov, A. A. Aksenov, and Minh Hai Nguyen. "The investigation of absolute flow non-uniform velocity distributions influence at the centrifugal compressor axial radial impeller inlet using numerical calculation methods in ANSYS CFX." E3S Web of Conferences 140 (2019): 05008. http://dx.doi.org/10.1051/e3sconf/201914005008.

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Currently, methods of numerical modelling are widely used. They are especially widely used in the design of turbo compressors. For the specific task of designing new flowing parts of a centrifugal compressor, it is not recommended to deviate from the canonical design techniques, but it is preferable to supplement them with numerical methods. This article is devoted to the end two-element stage investigation of a centrifugal compressor with an axial radial impeller; the stage main dimensions were obtained using the method of V.F. Rice. In order to obtain the necessary pressure characteristics a

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24

Borovkov, A. I., Yu B. Galerkin, О. А. Solovyeva, et al. "Methodology and Experience in the Primary Designing a Transsonic Axial Compressor." Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, no. 3 (142) (September 2022): 129–50. http://dx.doi.org/10.18698/0236-3941-2022-3-129-150.

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The article considers the basic principles underlying the program for the calculation and designing gas turbine engine axial compressors. Calculation of pressure losses and deflection ability of the cascades is based on the formulas of A. Komarov. The model involves empirical coefficients, the values of which were selected during program verification based on the results of testing multistage compressors and compressor stages. The basic equations and the algorithm for calculating pressures and velocities are given under the condition of radial balance. The application of computer programs base

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25

Dunham, J. "A New Endwall Model for Axial Compressor Throughflow Calculations." Journal of Turbomachinery 117, no. 4 (1995): 533–40. http://dx.doi.org/10.1115/1.2836565.

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It is well recognized that the endwall regions of a compressor—in which the annulus wall flow interacts with the mainstream flow—have a major influence on its efficiency and surge margin. Despite many attempts over the years to predict the very complex flow patterns in the endwall regions, current compressor design methods still rely largely on empirical estimates of the aerodynamic losses and flow angle deviations in these regions. This paper describes a new phenomenological model of the key endwall flow phenomena treated in a circumferentially averaged way. It starts from Hirsch and de Ruyck

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26

Jaeschke, Andrzej, and Grzegorz Liśkiewicz. "Sensitivity Study of Greitzer Model Based on Physical System Parameters of Radial Compressing Units." Energies 13, no. 19 (2020): 5111. http://dx.doi.org/10.3390/en13195111.

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Centrifugal compressors are key elements of energy systems and industrial installations including fluid flow. Their operating range is strictly limited by the surge phenomenon. The Greitzer model is a known way of simulating the compressor’s behaviour at the surge. In this paper, the parametric study of different versions of the Greitzer model is conducted. There are several versions of this model that include 4 to 2 equation models. The system behaviour depends on the features of the compressor itself as well as of the plenum. In this paper, all terms connected with the compressor were groupe

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27

Galerkin, Y. B., A. F. Rekstin, and O. A. Solovyeva. "Selecting the Dimensions of the Vaneless Diffuser of a Centrifugal Compressor Stage at the Primary Design Phase." Proceedings of Higher Educational Institutions. Маchine Building, no. 10 (715) (October 2019): 43–57. http://dx.doi.org/10.18698/0536-1044-2019-10-43-57.

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The advances in the primary design method of centrifugal compressors of the Universal Modeling Method have led to the need to analyze and revise the recommendations for the optimal size and configuration selection of vaneless diffusers of centrifugal compressor stages. The results of CFD calculations of a family of vaneless diffusers with different relative width, radial length, velocity coefficients and flow angles at the inlet are used to develop new recommendations. The choice of the optimal width of the vaneless diffuser is based on ensuring a non-separable flow in it at the boundary of th

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28

Lakshminarayana, B., M. Zaccaria, and B. Marathe. "The Structure of Tip Clearance Flow in Axial Flow Compressors." Journal of Turbomachinery 117, no. 3 (1995): 336–47. http://dx.doi.org/10.1115/1.2835667.

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Detailed measurements of the flow field in the tip region of an axial flow compressor rotor were carried out using a rotating five-hole probe. The axial, tangential, and radial components of relative velocity, as well as the static and stagnation pressures, were obtained at two axial locations, one at the rotor trailing edge, the other downstream of the rotor. The measurements were taken up to about 26 percent of the blade span from the blade tip. The data are interpreted to understand the complex nature of the flow in the tip region, which involves the interaction of the tip leakage flow, the

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29

Antas, Stanisław. "Exhaust System for Radial and Axial-Centrifugal Compressor with Pipe Diffuser." International Journal of Turbo & Jet-Engines 36, no. 3 (2019): 297–304. http://dx.doi.org/10.1515/tjj-2016-0068.

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Abstract The application of radial and axial-centrifugal compressors in turboprop, turboshaft and turbofan engines may require the construction of small diameters diffuser in order to obtain lower weight and smaller frontal area. Conventional exhaust diffusers typically have large outlet diameters for exit Mach numbers lower than 0,2 and low swirl flow to the combustor, hence the design of channel of the low-diameter diffusers called controlled-contour, fishtail-shaped diffuser or diffusing trumpet is complex. The cross-sectional shape of these channels is varied from circular to oval to ellip

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30

Hu, Li, Fu, Gu, Ren, and Lu. "Numerical Investigation of Flow and Heat Transfer in a Rotor-Stator Cavity with Centripetal Carbon Dioxide Through-Flow." Energies 12, no. 13 (2019): 2613. http://dx.doi.org/10.3390/en12132613.

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A centrifugal carbon dioxide compressor is a kind of general machine with extensive applications. The geometry of the side chambers of the compressors can be determined by studying the rotor-stator cavity with centripetal through-flow. In this paper, numerical simulations were conducted to predict the characteristics of flow and heat transfer. Three different speeds of rotation and two axial gap widths were considered. The correlations of the core swirl ratios were determined by fitting the results for two axial gap widths. The amounts of the moment coefficients of the disk were predicted. In

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31

Calvert, W. J., and R. B. Ginder. "Transonic fan and compressor design." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 213, no. 5 (1999): 419–36. http://dx.doi.org/10.1243/0954406991522671.

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Transonic fans and compressors are now widely used in gas turbine engines because of their benefits in terms of compactness and reduced weight and cost. However, careful and precise design is essential if high levels of performance are to be achieved. In this paper, the evolution of transonic compressor designs and methods is outlined, followed by more detailed descriptions of current compressor configurations and requirements and modern aerodynamic design methods and philosophies. Current procedures employ a range of methods to allow the designer to refine a new design progressively. Overall

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32

Engeda, Abraham, Yunbae Kim, Ronald Aungier, and Gregory Direnzi. "The Inlet Flow Structure of a Centrifugal Compressor Stage and Its Influence on the Compressor Performance." Journal of Fluids Engineering 125, no. 5 (2003): 779–85. http://dx.doi.org/10.1115/1.1601255.

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The performance of centrifugal compressors can be seriously degraded by inlet flow distortions that result from an unsatisfactory inlet configuration. In this present work, the flow is numerically simulated and the flow details are analyzed and discussed in order to understand the performance behavior of the compressor exposed to different inlet configurations. In a previous work, complementary to this present work, experimental tests were carried out for the comparison of a centrifugal compressor stage performance with two different inlet configurations: one of which was a straight pipe with

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33

Ziegler, Kai U., Heinz E. Gallus, and Reinhard Niehuis. "A Study on Impeller-Diffuser Interaction—Part II: Detailed Flow Analysis." Journal of Turbomachinery 125, no. 1 (2003): 183–92. http://dx.doi.org/10.1115/1.1516815.

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The interaction between impeller and diffuser is considered to have strong influence on the flow in centrifugal compressors. However, the knowledge about this influence is still not satisfying. This two-part paper presents an experimental investigation of the effect of impeller-diffuser interaction on the unsteady and the time-averaged flow field in impeller and diffuser and the performance of these components. The flat wedge vaned diffuser of the investigated compressor allows an independent adjustment of diffuser vane angle and radial gap between impeller exit and diffuser vane inlet. Attent

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34

Rabas, T. J., C. B. Panchal, and H. C. Stevens. "Integration and Optimization of the Gas Removal System for Hybrid-Cycle OTEC Power Plants." Journal of Solar Energy Engineering 112, no. 1 (1990): 19–28. http://dx.doi.org/10.1115/1.2930753.

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A preliminary design of the noncondensible gas removal system for a 10 MWe, land-based hybrid-cycle OTEC power plant has been developed and is presented herein. This gas removal system is very different from that used for conventional power plants because of the substantially larger and continuous noncondensible gas flow rates and lower condenser pressure levels which predicate the need for higher-efficiency components. Previous OTEC studies discussed the need for multiple high-efficiency compressors with intercoolers; however, no previous design effort was devoted to (a) the details of the in

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35

Shade, W. N., and D. E. Hampshire. "An Experimental Investigation of Oil-Buffered Shaft Seal Flow Rates." Journal of Engineering for Gas Turbines and Power 107, no. 1 (1985): 170–80. http://dx.doi.org/10.1115/1.3239679.

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An experimental investigation was conducted to identify an optimum oil-buffered shaft seal for use on centrifugal compressors, with the primary objective being minimal seal oil exposure to process gases that cause seal oil degradation or are toxic. Types of seals tested included smooth bore cylindrical bushings, spiral groove cylindrical bushings, radial outward-flow face seals, and radial inward-flow face seals. The influence of shaft speed, gas pressure, seal oil differential pressure, oil bypass flow rate, and oil supply temperature on process side seal oil flow rate was determined. The inv

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36

Margalida, Gabriel, Pierric Joseph, Olivier Roussette, and Antoine Dazin. "Comparison and Sensibility Analysis of Warning Parameters for Rotating Stall Detection in an Axial Compressor." International Journal of Turbomachinery, Propulsion and Power 5, no. 3 (2020): 16. http://dx.doi.org/10.3390/ijtpp5030016.

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The present paper aims at evaluating the surveillance parameters used for early stall warning in axial compressors, and is based on unsteady pressure measurements at the casing of a single stage axial compressor. Two parameters—Correlation and Root Mean Square (RMS)—are first compared and their relative performances discussed. The influence of sensor locations (in both radial and axial directions) is then considered, and the role of the compressor’s geometrical irregularities in the behavior of the indicators is clearly highlighted. The influence of the throttling process is also carefully ana

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37

Kalinkevych, M., V. Ihnatenko, O. Bolotnikova, and O. Obukhov. "Design of high efficiency centrifugal compressors stages." Refrigeration Engineering and Technology 54, no. 5 (2018): 4–9. http://dx.doi.org/10.15673/ret.v54i5.1239.

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The modern trend in compressor industry is an extension of the use of multi-shaft centrifugal compressors. Multi-shaft compressors have a number of advantages over single-shaft. The design of such compressors gives opportunity to use an axial inlet for all stages and select the optimum rotational speed for each pair of impellers, which, along with the cooling of the gas after each stage, makes possible to achieve high levels of efficiency. The design of high-efficiency centrifugal compressor stages can be performed on the basis of highly effective stage elements. Such elements are: impellers w

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38

Li, Y. S., and N. A. Cumpsty. "Mixing in Axial Flow Compressors: Part II—Measurements in a Single-Stage Compressor and a Duct." Journal of Turbomachinery 113, no. 2 (1991): 166–72. http://dx.doi.org/10.1115/1.2929076.

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This paper follows directly from Part I, which contains not only the description of the facilities and the results for the C106 four-stage compressor, but also the background, list of nomenclature, acknowledgments, and references. The discussion and conclusions for Parts I and II are given here. The single-stage compressor results show the significant effects of inlet guide vane (IGV) wakes on mixing across the stage in the so-called “free-stream” region; in the casing region tip clearance flow is shown to play an important role in mixing. Explanations for these results are given. Investigatio

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Skoch, Gary J. "Experimental Investigation of Diffuser Hub Injection to Improve Centrifugal Compressor Stability." Journal of Turbomachinery 127, no. 1 (2005): 107–17. http://dx.doi.org/10.1115/1.1812779.

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Results from a series of experiments to investigate whether centrifugal compressor stability could be improved by injecting air through the diffuser hub surface are reported. The research was conducted in a 4:1 pressure ratio centrifugal compressor configured with a vane-island diffuser. Injector nozzles were located just upstream of the leading edge of the diffuser vanes. Nozzle orientations were set to produce injected streams angled at −8, 0, and +8 degrees relative to the vane mean camber line. Several injection flow rates were tested using both an external air supply and recirculation fro

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Piesche, M., and L. Blum. "On compressible subsonic flow between impeller and casing of radial-flow compressors with superposed throughflow." Acta Mechanica 57, no. 3-4 (1985): 159–66. http://dx.doi.org/10.1007/bf01176915.

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Dong, Y., S. J. Gallimore, and H. P. Hodson. "Three-Dimensional Flows and Loss Reduction in Axial Compressors." Journal of Turbomachinery 109, no. 3 (1987): 354–61. http://dx.doi.org/10.1115/1.3262113.

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Measurements have been performed in a low-speed high-reaction single-stage axial compressor. Data obtained within and downstream of the rotor, when correlated with the results of other investigations, provide a link between the existence of suction surface–hub corner separations, their associated loss mechanisms, and blade loading. Within the stator, it has been shown that introducing a small clearance between the stator blade and the stationary hub increases the efficiency of the stator compared to the case with no clearance. Oil flow visualizaton indicated that the leakage reduced the extens

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Dring, R. P. "Radial Transport and Momentum Exchange in an Axial Compressor." Journal of Turbomachinery 115, no. 3 (1993): 477–86. http://dx.doi.org/10.1115/1.2929278.

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The objective of this work was to examine radial transport in axial compressors from two perspectives. The first was to compare the mixing coefficient based on a secondary flow model (using measured radial velocities) with that based on a turbulent diffusion model. The second was to use measured airfoil pressure forces and momentum changes to assess the validity of the assumption of diffusive radial transport, which is common to both models. These examinations were carried out at both design and off-design conditions as well as for two rotor tip clearances. In general it was seen that radial m

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Flete, Xavier, Nicolas Binder, Yannick Bousquet, and Sandrine Cros. "Numerical Investigation of Rotating Instability Development in a Wide Tip Gap Centrifugal Compressor." International Journal of Turbomachinery, Propulsion and Power 8, no. 3 (2023): 25. http://dx.doi.org/10.3390/ijtpp8030025.

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In the current study, full-stage unsteady simulations were performed to investigate rotating instability inception mechanisms in a particularly large tip clearance centrifugal compressor with a vaneless diffuser and a volute. Four operating points along a speed line were analysed to understand the influence of the mass flow reduction on flow structures. Close to the peak efficiency, an unsteady interaction between the tip clearance vortices and splitter blades was observed. Considering other studies, the influence of the tip gap size was analysed. Then, a large-scale vortex shedding from the l

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Han, Ge, Xingen Lu, Yanfeng Zhang, Shengfeng Zhao, Chengwu Yang, and Junqiang Zhu. "Investigation of two pipe diffuser configurations for a compact centrifugal compressor." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 4 (2017): 716–28. http://dx.doi.org/10.1177/0954410016685585.

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Diffusers are one of the most important factors determining the centrifugal compressor performance. The present work is aimed at providing a detailed understanding of the underlying flow and loss mechanisms in three different diffusers in a compact centrifugal compressor stage. Experimental and computational studies were conducted for various diffuser configurations, e.g. two pipe diffusers and one wedge diffuser, while keeping the throat in all the three geometries. It was found that both the pipe diffuser configurations had better aerodynamic performance than the original wedge diffuser. Fur

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Wennerstrom, A. J. "A Review of Predictive Efforts for Transport Phenomena in Axial Flow Compressors." Journal of Turbomachinery 113, no. 2 (1991): 175–79. http://dx.doi.org/10.1115/1.2929080.

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Transport phenomena as they apply to throughflow calculations in axial-flow compressors are reviewed. An historical background is presented. Then the debate raised by the Adkins and Smith versus the Gallimore and Cumpsty approaches to radial transport is discussed. This debate was resolved in that it was finally concluded that both turbulent transport and convective secondary flows play a role in spanwise transport. Other major related efforts mentioned are those of Hirsch and his colleagues and Papailiou and his colleagues. Readers are encouraged to reconsider exploitation of the work of Kerr

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Drozdov, A. A., Y. B. Galerkin, and A. A. Utsekhovskiy. "Development and Implementation of a New Mathematical Model of the Tangential Exit Nozzles in Centrifugal Compressors." Proceedings of Higher Educational Institutions. Маchine Building, no. 06 (723) (June 2020): 17–35. http://dx.doi.org/10.18698/0536-1044-2020-6-17-35.

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Various engineering techniques are used for optimal gas-dynamic design of centrifugal compressors. This includes a universal modelling method that consists of software programs developed at Peter the Great St. Petersburg Polytechnic University. Tangential exit nozzles are elements of the centrifugal compressor flow path. The analysis of the results of the tangential exit nozzle calculations using the current mathematical model showed a need of improvement. The following main provisions formed a basis for a new model: the size of the passage is determined using the flow rate equation at the ent

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Ma, Y., A. Engeda, M. Cave, and J.-L. Di Liberti. "Improved centrifugal compressor impeller optimization with a radial basis function network and principle component analysis." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 224, no. 4 (2010): 935–45. http://dx.doi.org/10.1243/09544062jmes1635.

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The development of a fast and reliable computer-aided design and optimization procedure for centrifugal compressors has attracted a great deal of attention both in the industry and in academia. Artificial neural networks (ANNs) have been widely used to create an approximate performance map to substitute the direct application of flow solvers in the optimization procedure. Although ANNs greatly decrease the computational time for the optimization, their accuracies still limit their applications. Furthermore, ANNs also bring errors to the final results. In this study, principal component analysi

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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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Frank, Roman G., Christian Wacker, and Reinhard Niehuis. "Loss Characterization of a Conventional Variable Inlet Guide Vane." International Journal of Turbomachinery, Propulsion and Power 6, no. 3 (2021): 30. http://dx.doi.org/10.3390/ijtpp6030030.

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Variable inlet guide vanes (VIGVs) are most commonly used as the major control unit of integrally geared centrifugal compressors (IGCCs). In order to enhance the efficient operating range of the compressor, the loss mechanisms and utilization limits of state-of-the-art VIGVs need to be better understood. Field measurements in the wake of a typical, commercially used configuration were therefore conducted at the VIGV test facility of the Bundeswehr University Munich. The investigations were carried out at application oriented subsonic flow conditions and stagger angles from 50∘ to 90∘ covering

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Dragan, Valeriu, Oana Dumitrescu, Ion Malael, and Adrian Daniel Azoitei. "Rake impact on turboshaft compressors, a numerical study." Aircraft Engineering and Aerospace Technology 92, no. 8 (2020): 1169–76. http://dx.doi.org/10.1108/aeat-01-2020-0022.

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Purpose Turboshaft engines usually include one centrifugal compressor due to its high-pressure ratio, stability and compactness. Many designers rely on positive raking to decrease tip gap flow and therefore losses. However recent optimization studies revealed geometries contradicting this canonic view. Hence, this paper aims to investigate how the rake angle alone can influence performance and to which extent. Design/methodology/approach A turboshaft representative impeller was chosen and altered for null and +/−30° rake angles. Menter's shear stress transport model is used for steady computat

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