Relevant bibliographies by topics / Axial flow compressors. Compressors. Aerodynamics

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Axial flow compressors. Compressors. Aerodynamics'

Author: Grafiati
Published: 4 June 2021
Last updated: 7 February 2022

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Journal articles on the topic "Axial flow compressors. Compressors. Aerodynamics"

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Zhang, Yingying, and Shijie Zhang. "Performance prediction of transonic axial multistage compressor based on one-dimensional meanline method." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (February 25, 2021): 1355–69. http://dx.doi.org/10.1177/0957650921998819.

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This study proposes a 1D meanline program for the modeling of modern transonic axial multistage compressors. In this method, an improved blockage factor model is proposed. Work-done factor that varies with the compressor performance conditions is added in this program, and at the same time a notional blockage factor is kept. The coefficient of deviation angle model is tuned according to experimental data. In addition, two surge methods that originated from different sources are chosen to add in and compare with the new method called mass flow separation method. The salient issues presented here deal first with the construction of the compressor program. Three well-documented National Aerodynamics and Space Administration (NASA) axial transonic compressors are calculated, and the speedlines and aerodynamic parameters are compared with the experimental data to verify the reliability and robustness of the proposed method. Results show that consistent agreement can be obtained with such a performance prediction program. It was also apparent that the two common methods of surge prediction, which rely upon either stage or overall characteristic gradients, gave less agreement than the method called mass flow separation method.
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Hall, E. J. "Aerodynamic modelling of multistage compressor flow fields Part 1: Analysis of rotor-stator-rotor aerodynamic interaction." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 2 (February 1, 1998): 77–89. http://dx.doi.org/10.1243/0954410981532153.

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The primary purpose of this study was to investigate improved numerical techniques for predicting flows through multistage compressors. The vehicle chosen for this study was the Pennsylvania State University Research Compressor (PSRC). The PSRC facility consists of a 3 1/2-stage axial flow compressor which shares design features which are consistent with embedded stages of modern gas turbine engine axial flow compressors. In Part 1 of this two-part paper, several computational fluid dynamics techniques were applied to predict both steady and unsteady flows through the PSRC facility. Interblade row coupling via a circumferentially averaged mixing-plane approach was employed for steady flow analysis. A mesh density sensitivity study was performed to define the minimum mesh requirements necessary to achieve reasonable agreement with the experimental data. Time-dependent flow predictions were performed using a time-dependent interblade row coupling technique. These calculations evaluated the aerodynamic interactions occurring between rotor 2, stator 2 and rotor 3 for the PSRC rig.
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Gallimore, S. J., and N. A. Cumpsty. "Spanwise Mixing in Multistage Axial Flow Compressors: Part I—Experimental Investigation." Journal of Turbomachinery 108, no. 1 (July 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 wakes.
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Kang, Qiang, Shuguang Zuo, and Kaijun Wei. "Study on the aerodynamic noise of internal flow of regenerative flow compressors for a fuel-cell car." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 228, no. 7 (August 30, 2013): 1155–74. http://dx.doi.org/10.1177/0954406213500746.

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The regenerative flow compressor used in fuel-cell cars generates high aerodynamic noise, which is the main source of noise. Compared with the research on centrifugal or axial turbomachinery, research on the noise of regenerative flow compressors is far from adequate. This paper presents the on-going work on it at Tongji University based on both experimental and computational works. In this study, a three-dimensional unsteady computational fluid dynamic model of the compressor was constructed with the large eddy approach. The pressure fluctuation, vortex noise source and Ffowcs William-Hawkings (FW-H) method were used to analyze the characteristics of the aerodynamic noise sources. Additionally, the far-field aerodynamic noise generated by the internal flow of the compressor was predicted using the aeroacoustic finite element method. The simulation results were validated with the experimental data. It was found that combining the fluid dynamic model and aeroacoustic finite element analysis promising results for aerodynamic noise prediction of compressors could be produced. The effects of the impeller parameters on the aerodynamic noise of the compressor were also studied.
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Li, Chang Zheng, and Yong Lei. "Compressor Surge Detection Based on Support Vector Data Description." Applied Mechanics and Materials 152-154 (January 2012): 1545–49. http://dx.doi.org/10.4028/www.scientific.net/amm.152-154.1545.

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Axial flow compressors work as an indispensable device in industry fields. Surge is a phenomenon of aerodynamic instability, which characterized by disruption of flow. When a compressor works in surge state, the vibration is so intense that it may causes accidents. Detecting surge timely and accurately not only insure safety of compressors but also is a key of active control of aerodynamic instability. Support vector data description (SVDD) is a one-class classification method developed based on the theory of support vector machine (SVM). In this paper, we introduce SVDD into the field of compressor surge detection. It demonstrates that SVDD method can give a warning far ahead of surge.
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Kulyk, Mykola, Ivan Lastivka, and Yuri Tereshchenko. "EFFECT OF HYSTERESIS IN AXIAL COMPRESSORS OF GAS-TURBINE ENGINES." Aviation 16, no. 4 (December 24, 2012): 97–102. http://dx.doi.org/10.3846/16487788.2012.753679.

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The phenomenon of separated flow hysteresis in the process of the streamlining the axial compressor of gas-turbine engines is considered. Generalised results of research on the occurrence of hysteresis in the aerodynamic performance of compressor grids and its influence on the performance of the bladed disks of compressors that operate in real conditions of periodic circular non-uniformity are demonstrated.
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Storace, A. F., D. C. Wisler, H. W. Shin, B. F. Beacher, F. F. Ehrich, Z. S. Spakovszky, M. Martinez-Sanchez, and S. J. Song. "Unsteady Flow and Whirl-Inducing Forces in Axial-Flow Compressors: Part I—Experiment." Journal of Turbomachinery 123, no. 3 (February 1, 2000): 433–45. http://dx.doi.org/10.1115/1.1378299.

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An experimental and theoretical investigation has been conducted to evaluate the effects seen in axial-flow compressors when the centerline of the rotor is displaced from the centerline of the static structure of the engine. This creates circumferentially nonuniform rotor-tip clearances, unsteady flow, and potentially increased clearances if the rotating and stationary parts come in contact. The result not only adversely affects compressor stall margin, pressure rise capability, and efficiency, but also generates an unsteady, destabilizing, aerodynamic force, called the Thomas/Alford force, which contributes significantly to rotor whirl instabilities in turbomachinery. Determining both the direction and magnitude of this force in compressors, relative to those in turbines, is especially important for the design of mechanically stable turbomachinery components. Part I of this two-part paper addresses these issues experimentally and Part II presents analyses from relevant computational models. Our results clearly show that the Thomas/Alford force can promote significant backward rotor whirl over much of the operating range of modern compressors, although some regions of zero and forward whirl were found near the design point. This is the first time that definitive measurements, coupled with compelling analyses, have been reported in the literature to resolve the long-standing disparity in findings concerning the direction and magnitude of whirl-inducing forces important in the design of modern axial-flow compressors.
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Ho¨nen, H., and H. E. Gallus. "Monitoring of Aerodynamic Load and Detection of Stall in Multistage Axial Compressors." Journal of Turbomachinery 117, no. 1 (January 1, 1995): 81–86. http://dx.doi.org/10.1115/1.2835645.

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The unsteady flow in a single-stage axial flow compressor at different operating conditions has been investigated with hot-wire and hot-film probes to find out the influence of the aerodynamic compressor load on the periodic fluctuations. These results are compared with measurements in the last stages of a multistage high-pressure compressor of a gas turbine for normal operation and under stall conditions. From the patterns of the frequency spectra of the measuring signals a parameter for the detection of the approach to the stability line of a compressor is derived. A method for the on-line monitoring of the aerodynamic load is presented. Based on these results a monitoring system has been developed. First experiences with this system, applied to two multistage compressors, are reported.
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Wisler, D. C. "Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing." Journal of Engineering for Gas Turbines and Power 107, no. 2 (April 1, 1985): 354–63. http://dx.doi.org/10.1115/1.3239730.

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A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers, flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.
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Zhang, Botao, Xiaochen Mao, Xiaoxiong Wu, and Bo Liu. "Effects of Tip Leakage Flow on the Aerodynamic Performance and Stability of an Axial-Flow Transonic Compressor Stage." Energies 14, no. 14 (July 10, 2021): 4168. http://dx.doi.org/10.3390/en14144168.

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To explain the effect of tip leakage flow on the performance of an axial-flow transonic compressor, the compressors with different rotor tip clearances were studied numerically. The results show that as the rotor tip clearance increases, the leakage flow intensity is increased, the shock wave position is moved backward, and the interaction between the tip leakage vortex and shock wave is intensified, while that between the boundary layer and shock wave is weakened. Most of all, the stall mechanisms of the compressors with varying rotor tip clearances are different. The clearance leakage flow is the main cause of the rotating stall under large rotor tip clearance. However, the stall form for the compressor with half of the designed tip clearance is caused by the joint action of the rotor tip stall caused by the leakage flow spillage at the blade leading edge and the whole blade span stall caused by the separation of the boundary layer of the rotor and the stator passage. Within the investigated varied range, when the rotor tip clearance size is half of the design, the compressor performance is improved best, and the peak efficiency and stall margin are increased by 0.2% and 3.5%, respectively.
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Dissertations / Theses on the topic "Axial flow compressors. Compressors. Aerodynamics"

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Zaki, Mina Adel. "Physics based modeling of axial compressor stall." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/31683.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2010.
Committee Chair: Dr. Lakshmi N. Sankar; Committee Member: Dr. Alex Stein; Committee Member: Dr. J.V. R. Prasad; Committee Member: Dr. Richard Gaeta; Committee Member: Dr. Suresh Menon. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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DiPietro, Anthony Louis. "Effects of temperature transients on the stall and stall recovery aerodynamics of a multi-stage axial flow compressor." Diss., This resource online, 1997. http://scholar.lib.vt.edu/theses/available/etd-10052007-143638/.

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Rivera-Cedeno, Carlos J. "Numerical simulation of dynamic stall phenomena in axial flow compressor blade rows." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12405.

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Nowinski, Matthew C. "A two-dimensional model to predict rotating stall in axial-flow compressors." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-08042009-040420/.

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Cousins, William T. "The Dynamics of Stall and Surge Behavior in Axial-Centrifugal Compressors." Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/29794.

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The phenomena of stall and surge in axial-centrifugal compressors is investigated through high-response measurements of both the pressure field and the flowfield throughout the surge cycle. A unique high-response forward-facing and aft-facing probe provides flow information. Several axial-centrifugal compressors are examined, both in compressor rigs and engines. Extensive discussion is presented on the differences in axial and centrifugal rotors and their effect on the system response characteristics. The loading parameters of both are examined and data is presented that shows the increased tolerance of the centrifugal stage to instability. The dynamics of the compressor blade response are shown to be related to the transport time of a fluid particle moving through a blade passage. The data presented provides new insight into the dynamic interactions that occur prior to and during stall and surge. In addition, the inception of rotating stall and the inception of surge are shown to be the same phenomena . An analytical dynamic model (DYNTECC) is applied to one of the compression systems and the results are compared to data. The results show that the model can capture the global effects of rotating stall and surge. The data presented, along with the analytical results, provide useful information for the design of active and passive stall control systems.
Ph. D.
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Akhlaghi, Mohammad. "Application of a vane-recessed tubular-passage casing treatment to a multistage axial-flow compressor." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/11401.

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The current study investigates a range of issues relating to the use of a vane-recessed tubular-passage casing treatment as a passive stall control technique in a multistage axial-flow compressor. The focus of the research was to determine whether such a treatment could delay the initiation of stall at lower mass flow rates as well as providing the most beneficial improvement in flow characteristics without sacrificing compressor efficiencies. Specific objectives of this study were to examine possible improvements or deterioration in the flow characteristics including stall margin, peak pressure rise coefficients and maximum efficiency in a multistage axial flow compressor. A casing treatment in addition to several spacer rings was developed from two initial designs and tested on the first stage of a low speed three-stage axial-flow compressor with a (0.7) hub to tip diameter ratio. The treatment configuration consisted of three parts: an outer casing ring, with a tubular shaped passage on the inside diameter, a set of 120 evenly spaced curved vanes, and a shroud or inner ring. The casing treatment was positioned following the inlet guide vanes upstream and partly covering the tip of the rotor blades. The main parts of the casing treatment including the recessed vanes in addition to some of the spacer rings were manufactured from high quality acrylic. Eight additional spacer rings of various shapes and geometry were added. The first ring held and partly covered the IGVs, in front of the casing treatment. The rotor tip exposure ratio was thought to have a significant impact on the effectiveness of the casing treatment. Therefore the other seven rings were used to provide the desired uncovered region of the rotor tip axial chord of about 10% in order to provide a range of exposures of (23.2%, 33.3%, 43.4%, 53.5%, 63.6%, 73.7%, and 83.8%). The results showed significant improvements in stall margin in all treated casing configurations along with insignificant efficiency sacrifices in some compressor builds. About (28.56%) of stall margin improvement in terms of corrected mass flow rate was achieved using a casing treatment with a (33.3%) rotor tip exposure. The compressor build with (0.535) rotor exposure ratios was the best configuration in terms of efficiency gain and loss characteristics. This build was able to provide the highest values of the maximum efficiencies in comparison with the performance achieved from the solid casing. An improvement of (1.81%) in the maximum efficiency in terms of the overall total-total pressure ratio, in association with a (22.54%) stall margin improvement in terms of the corrected mass flow rates were achieved by the application of this treatment configuration. The improvement in the peak pressure rise coefficients in terms of the overall total-total pressure ratio, obtained from this build was (2.33%). The compressor configuration using a casing treatment with a (0.636) rotor exposure ratio was the best build in terms of the pressure rise coefficients. This configuration was able to provide highest value of the peak pressure rise in comparison with the characteristics achieved from the datum build. An improvement of (2.65%) in the peak pressure rise coefficient in terms of the overall total-total pressure ratio, in association with a (22.49%) improvement in stall margin in terms of the corrected mass flow rates was achieved from this casing treatment build. The improvement in maximum efficiency in terms of the overall total-total pressure ratio, obtained from this build was (1.03%). The results suggest that the vane-recessed tubular-passage casing treatment designed as part of this investigation achieved the objectives, which were established for the research. In the majority of instances it not only produced gains in flow range, pressure rise coefficients and efficiencies, but also enabled the rotating stall, which developed at much lower mass flow rates in the compressor, to become progressive rather than abrupt.
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Fourie, Neil. "Simulating the effect of wind on the performance of axial flow fans in air-cooled steam condenser systems." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/95977.

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Thesis (MEng) -- Stellenbosch University, 2014.
ENGLISH ABSTRACT: The use of air-cooled steam condensers (ACSCs) is the preferred cooling method in the chemical and power industry due to stringent environmental and water use regulations. The performance of ACSCs is however highly dependent on the influence of windy conditions. Research has shown that the presence of wind reduces the performance of ACSCs. It has been found that cross-winds (wind perpendicular to the longest side of the ACSC) cause distorted inlet flow conditions, particularly at the upstream peripheral fans near the symmetry plane of the ACSC. These fans are subjected to what is referred to as '2-D' wind conditions, which are characterised by flow separation on the upstream edge of the fan inlets. Experimental investigations into inlet flow distortion have simulated these conditions by varying the fan platform height. Low platform heights resulted in higher levels of inlet flow distortion, as also found to exist with high cross-wind speeds. This investigation determines the performance of various fan configurations (representative of configurations used in the South- African power industry) subjected to distorted inlet flow conditions through experimental and numerical investigations. The similarity between platform height and cross-wind effects is also investigated and a correlation between system volumetric effectiveness, platform height and cross-wind velocity is found.
AFRIKAANSE OPSOMMING: Die gebruik van lugverkoelde stoom kondensors (LVSK's) word verkies as 'n verkoelingsmetode in die chemiese- en kragvoorsieningsindustrie as gevolg van streng omgewings- en waterverbruiksregulasies. Die werkverrigting van LVSK's word egter grootliks beïnvloed deur die teenwoordigheid van wind. Navorsing het gewys dat die teenwoordigheid van wind die werkverrigting van LVSK's verminder. Daar was gevind dat kruiswinde (wind loodreg tot die langste sy van die LVSK) versteurde inlaat vloeitoestande veroorsaak, veral by waaiers wat aan die stroomop kant van die LVSK naby die simmetrievlak geleë is. Hierdie waaiers word blootgestel aan na wat verwys word as '2-D' windtoestande wat gekenmerk word deur vloeiwegbreking wat plaasvind by die stroomop rand van die waaierinlate. Eksperimentele ondersoeke van inlaat vloeiversteurings het hierdie toestande gesimuleer deur die waaier platformhoogte te verstel. Lae platform hoogtes het gelei tot hoër vlakke van inlaat vloeiversteuring, soortgelyk aan wat gevind word met hoë kruiswindsnelhede. Hierdie ondersoek gebruik numeriese en eksperimentele metodes om die werkverrigting van verskeie waaierkon gurasies (verteenwoordigend van kon- gurasies wat gebruik word in die Suid-Afrikaanse kragvoorsieningsindustrie) wat blootgestel word aan versteurde inlaat vloeitoestande te bepaal. Die ooreenkoms tussen platformhoogte en kruiswind e ekte word ook ondersoek en 'n korrelasie tussen die sisteem volumetriese e ektiwiteit, platformhoogte en kruiswindsnelheid word bepaal.
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Grimshaw, Samuel David. "Bleed in axial compressors." Thesis, University of Cambridge, 2014. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.707970.

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Power, Bronwyn. "Aspirated compressors." Thesis, University of Cambridge, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.648363.

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Li, Yan Sheng. "Mixing in axial compressors." Thesis, University of Cambridge, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.334235.

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Books on the topic "Axial flow compressors. Compressors. Aerodynamics"

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Paduano, James D. Active control of rotating stall in axial compressors. Cambridge, Mass: Gas Turbine Laboratory, Massachusetts Institute of Technology, 1992.

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Cyrus, Václav. Secondary flow in axial compressors and its effect on aerodynamic characteristics. Praha: National Research Institute for Machine Design, Praha-Běchovice, 1988.

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Axial-flow compressors: A strategy for aerodynamic design and analysis. New York: ASME Press, 2003.

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Gysling, Daniel L. Dynamic control of rotating stall in axial flow compressors using aeromechanical feedback. Cambridge, Mass: Gas Turbine Laboratory, Massachusetts Institute of Technology, 1993.

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Haynes, Joel M. Active control of rotating stall in a three-stage axial compressor. Cambridge, Mass: Gas Turbine Laboratory, Massachusetts Institute of Technology, 1993.

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Time-marching: A step-by-step guide to a flow solver. Aldershot, Hants., England: Ashgate, 1997.

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Ng, Y. K. Eddie. Compressor instability with integral methods. Berlin: Springer, 2007.

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Nichols, Jason C. A three-dimensional multi-block Newton-Krylov flow solver for the Euler equations. [Downsview, Ont: University of Toronto, Institute for Aerospace Studies], 2004.

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Schmidt, James F. Off-design computer code for calculating the aerodynamic performance of axial-flow fans and compressors: User's manual. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

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Buisine, D. Modelisation du grand decrochage dans les compresseurs axiaux. Rhode Saint Genese, Belgium: Von Karman Institute for Fluid Dynamics, 1988.

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Book chapters on the topic "Axial flow compressors. Compressors. Aerodynamics"

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Breugelmans, F. A. E. "Unsteady Flow in Axial Flow Compressors." In Modern Research Topics in Aerospace Propulsion, 275–95. New York, NY: Springer New York, 1991. http://dx.doi.org/10.1007/978-1-4612-0945-4_15.

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Serovy, George K. "Secondary Flows in Axial-Flow Compressors." In Thermodynamics and Fluid Mechanics of Turbomachinery, 601–19. Dordrecht: Springer Netherlands, 1985. http://dx.doi.org/10.1007/978-94-009-5153-2_17.

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Gambini, Marco, and Michela Vellini. "Preliminary Design of Axial Flow Compressors." In Springer Tracts in Mechanical Engineering, 155–97. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-51299-6_4.

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Sultanian, Bijay K. "Axial-Flow Pumps, Fans, and Compressors." In Fluid Mechanics and Turbomachinery, 225–60. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-10.

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Sentker, A., and W. Riess. "Unsteady Flow and Turbulence in a Low Speed Axial Compressor." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 273–86. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_18.

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Parrish, C. J. "Dynamic Tip Clearance Measurements in Axial Flow Compressors." In COMADEM 89 International, 419–23. Boston, MA: Springer US, 1989. http://dx.doi.org/10.1007/978-1-4684-8905-7_65.

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Gallus, H. E., C. A. Poensgen, and J. Zeschky. "Three-Dimensional Unsteady Flow in a Single Stage Axial-Flow Turbine and Compressor." In Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, 487–505. New York, NY: Springer New York, 1993. http://dx.doi.org/10.1007/978-1-4613-9341-2_24.

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Hosny, W. M., L. Leventhal, and W. G. Steenken. "A Study of Active Dither Control of Aerodynamic Instabilities in Axial - Compressors." In Instabilities and Turbulence in Engineering Flows, 129–49. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1743-2_7.

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Sánchez-Parra, Marino, and René Vite-Hernández. "Use of a Rule-Based System for Process Control: Flow Instabilities in Axial Compressors Case Study." In MICAI 2002: Advances in Artificial Intelligence, 494–505. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/3-540-46016-0_52.

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Sari, Gholam-Reza, Ouassima Akhrif, and Lahcen Saydy. "Bifurcation Analysis and Active Control of Surge and Rotating Stall in Axial Flow Compressors via Passivity." In Informatics in Control, Automation and Robotics, 91–116. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-55011-4_5.

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Conference papers on the topic "Axial flow compressors. Compressors. Aerodynamics"

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Storer, J. A., and N. A. Cumpsty. "Tip Leakage Flow in Axial Compressors." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-127.

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Experimental measurements in a linear cascade with tip clearance are complemented by numerical solutions of the three-dimensional Navier-Stokes equations in an investigation of tip leakage flow. Measurements reveal that the clearance flow, which separates near the entry of the tip gap, remains unattached for the majority of the blade chord when the tip clearance is similar to that typical of a machine. The numerical predictions of leakage flow rate agree very well with measurements and detailed comparisons show that the mechanism of tip leakage is primarily inviscid. It is demonstrated by simple calculation that it is the static pressure field near the end of the blade which controls chordwise distribution of the flow across the tip. Although the presence of a vortex caused by the roll-up of the leakage flow may affect the local pressure field, the overall magnitude of the tip leakage flow remains strongly related to the aerodynamic loading of the blades.
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Gundy-Burlet, Karen L., and Daniel J. Dorney. "Physics of Airfoil Clocking in Axial Compressors." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-444.

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Axial compressors have inherently unsteady flow fields because of relative motion between rotor and statnr airfnils. This relative motion leads to viscous and inviscid (potential) interactions between blade rows. As the number of stages increases in a turbomachine, the buildup of convected wakes can lead in progressively more complex wake/wake and wake/airfnil interactions. Variations in the relative circumferential positions of stators or rotors can change these interactions, leading to different unsteady forcing functions on airfoils and different compressor efficiencies. The current study uses an unsteady, two-dimensional thin-layer Navier-Stokes zonal approach to investigate the unsteady aerodynamics of stator clocking in a low-speed 2 ½-stage compressor. Relative motion between rotors and stators is made possible by the use of systems of patched and overlaid grids. Results include surface pressures instantaneous forces and efficiencies for a 2 ½-stage compressor configuration.
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3

Banjac, Milan, Milan V. Petrovic, and Alexander Wiedermann. "Multistage Axial Compressor Flow Field Predictions Using CFD and Through-Flow Calculations." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57632.

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A comparison between two different methods for aerodynamic calculation of multistage axial compressors is presented. Results obtained using classical 2D through-flow calculations were compared with CFD results for several test cases, including various subsonic and supersonic multistage axial compressors with different geometric configurations and stage operating parameters. Calculated flow fields were compared in terms of overall compressor performances, individual blade row operation parameters and spanwise distributions of different flow variables. Nominal and off-design compressor operating conditions were analyzed and all the results were compared with experimental data. Accuracy, advantages and differences between individual methods are discussed.
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4

Day, Ivor, John Williams, and Christopher Freeman. "Rain Ingestion in Axial Flow Compressors at Part Speed." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68582.

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New experimental work is reported on the effects of water ingestion on the performance of an axial flow compressor. The background to the work is the effect which heavy rain has on an aero-engine compressor when operating in ‘descent idle’ mode, i.e. when the compressor is operating at part-speed and when the aero-mechanical effects of water ingestion are likely to be more important than the thermodynamic effects. Most of our existing knowledge in this field comes from whole engine tests. The current work provides the first known results from direct measurements on a stand-alone compressor. The influence of droplet size on path trajectory is considered both computationally and experimentally to show that most rain droplets will collide with the first row of rotor blades. The water on the blades is then centrifuged towards the casing where the normal air flow patterns in the vicinity of the rotor tips are disrupted. The result of this disruption is a reduction in the delivery pressure and an increase the torque required to drive the compressor. Both effects reduce the efficiency of the machine. The behaviour of the water in the blade rows is examined in detail, and simple models are proposed to explain the loss of pressure rise and the increase in torque. The measurement were obtained in a low speed compressor making it possible to study the mechanical (increase in torque) and aerodynamic (reduction in pressure rise) effects of water ingestion without the added complication of thermodynamic effects.
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5

Bruni, Giuseppe, James Taylor, Senthil Krishnababu, Robert Miller, and Roger Wells. "Squealer Tip Treatment Design for Axial Compressors." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14906.

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Abstract End-wall flows are amongst the main sources of losses in the rear stages of a typical multi-stage axial compressor. Reducing the tip leakage losses in the rotor blades and vanes can provide an increased efficiency and stall margin of a given axial compressor stage. One approach is to use squealer tips, which are traditionally designed to minimize the effect of tip rubbing. However, squealers can also provide a significant performance benefit, when designed considering aerodynamics from the beginning, as shown in this paper. A CFD based methodology, in which the blade or vane thickness distribution is varied in a controlled manner was developed. This design methodology was used to create different types of squealer tip geometry for a representative stage in a low speed compressor rig. Three different tip concepts were designed, based on a Suction Side Squealer, on a Pressure Side Squealer and on the combination of the two being merged between the leading edge and trailing edge, this new design is called the SuPr Tip. Subsequent experimental tests carried out agreed with the predicted relative ranking of the different squealer designs and on the superior performance of the SuPr tip design over the others, thus validating the methodology and the design process.
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6

Illana, Enric, Nicholas Grech, Pavlos K. Zachos, and Vassilios Pachidis. "Axial Compressor Aerodynamics Under Sub-Idle Conditions." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94368.

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With stricter regulations on engine altitude relight capability, the understanding of low-speed axial compressor performance is becoming increasingly important. At such far off-design conditions, compressors behave differently from design point, with large changes in the flow phenomena and reduced reliability on the established empirical equations and assumptions. This work focuses on the aerodynamics of a locked-rotor axial compressor at high inlet Mach number conditions, using a validated numerical simulation approach. In a locked-rotor compressor there is very little compression of the inflow. The air is forced to accelerate, with the rear stages seeing the highest velocities. Depending on the inlet Mach number, the velocity at the rear stages can be close to sonic, until choking conditions are reached. To predict accurately the zero-speed compressor performance close to the choking point, the corresponding blade aerodynamic coefficients are evaluated as a function of the blade’s physical parameters and the inlet Mach number. In addition, the blockage due to the separated flow as a result of the high negative incidences is investigated as a function of inlet Mach number, incidence, solidity and stagger angle. Models that predict the characteristics and choking mass flow of the compressor, require such data. This work offers a better insight into the low-speed and locked rotor characteristics of the compressor. The zero-speed line can be calculated through a stage-stacking technique using the aerodynamic coefficients and flow blockage derived from the numerical simulations. Low-speed lines between the zero and idle-speed line can subsequently be created through interpolation. Using this methodology, it is possible to generate a complete sub-idle map for a multi-stage axial compressor, enhancing the predictive capability of whole engine performance solvers.
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7

Spakovszky, Z. S. "Analysis of Aerodynamically Induced Whirling Forces in Axial Flow Compressors." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0418.

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A new analytical model to predict the aerodynamic forces in axial flow compressors due to asymmetric tip-clearance is introduced. The model captures the effects of tip-clearance induced distortion (i.e. forced shaft whirl), unsteady momentum-induced tangential blade forces and pressure induced forces on the spool. Pressure forces are shown to lag the tip-clearance asymmetry, resulting in a tangential (i.e. whirl-inducing) force due to spool pressure. This force can be of comparable magnitude to the classical Alford force. Prediction and elucidation of the Alford force is also presented. In particular, a new parameter denoted as the blade loading indicator is deduced. This parameter depends only on stage geometry and mean flow and determines the direction of whirl tendency due to tangential blade loading forces in both compressors and turbines. All findings are suitable for incorporation into an overall dynamic system analysis and integration into existing engine design tools.
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8

Li, Bo, Chun-wei Gu, Xiao-tang Li, Tai-qiu Liu, and Yao-bing Xiao. "Development of a Throughflow Method for Aerodynamic Analysis of Highly Loaded Axial Flow Compressors." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42020.

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In this paper, a novel engineering platform for throughflow analysis based on streamline curvature approach is developed for the research of a 5-stage compressor. It includes several types of improved loss and deviation angle models for the purpose of reflecting the influences of three-dimensional internal flow in highly loaded multistage compressors with higher accuracy. A spanwise mixing model considering viscous shear force with a no-slip condition is applied to improve assessment about the substantial amounts of radial energy and momentum exchange, a shock model accounting for shock geometry changes is also contained to better simulate transonic flow near the tip regions. In order to validate the reliability and robustness of the method, series of test cases including a subsonic compressor P&W 3S1, a transonic rotor NASA Rotor 1B and especially an advanced high pressure core compressor GE E3 HPC have been conducted. Then the computation procedure is applied to the research of a 5-stage compressor which is designed for developing an industry gas turbine. The overall performance and aerodynamic configuration predicted by the procedure both at design- and part-speed conditions are analyzed and compared with experimental results, which show a good agreement. The throughflow method is verified as a reliable and convenient tool for aerodynamic design and performance prediction of modern highly loaded compressors. It is also qualified for further optimization of the 5-stage compressor.
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Ehrich, F. F., Z. S. Spakovszky, M. Martinez-Sanchez, S. J. Song, D. C. Wisler, A. F. Storace, H. W. Shin, and B. F. Beacher. "Unsteady Flow and Whirl-Inducing Forces in Axial-Flow Compressors: Part II — Analysis." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0566.

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An experimental and theoretical investigation was conducted to evaluate the effects seen in axial-flow compressors when the centerline of the rotor becomes displaced from the centerline of the static structure of the engine, thus creating circumferentially non-uniform, rotor-tip clearances. This displacement produces unsteady flow and creates a system of destabilizing forces, which contribute significantly to rotor whirl instability in turbomachinery. These forces were first identified by Thomas (1958) for turbines and by Alford (1965) for jet engines. In Part I, the results from an experimental investigation of these phenomena were presented. In this Part II, three analytic models were used to predict both the magnitude and direction of the Thomas/Alford force in its normalized form, known as the β coefficient, and the unsteady effects for the compressors tested in Part I. In addition, the effects of a whirling shaft were simulated to evaluate differences between a rotor with static off-set and an actual whirling eccentric rotor. The models were also used to assess the influence of the non-axisymmetric static pressure distribution on the rotor spool, which was not measured in the experiment. The models evaluated were: (1) the Two-Sector Parallel Compressor (2SPC) model (Ehrich, 1993), (2) the Infinite-Segment-Parallel-Compressor (ISPC) model (Spakovszky, 2000), and (3) the Two-Coupled Actuator Disc (2CAD) model (Song and Cho, 2000). The results of these analyses were found to be in agreement with the experimental data in both sign and trend. Thus, the validated models provide the general means to predict the aerodynamic destabilizing forces for axial flow compressors in turbine engines. These tools have the potential to improve the design of rotordynamically stable turbomachinery.
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10

Shan, Peng. "Kinematic Analysis of 3-D Swept Shock Surfaces in Axial Flow Compressors." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0492.

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This paper is Part II of a comprehensive study on the blade leading edge sweep/bend of supersonic and transonic axial compressors. The paper explores and analyses the kinematic characteristic variables of 3-D swept shock surfaces. In the research field called sweep aerodynamics of axial flow compressors and fans, many types of high loading swept blades are under an intensive study. So, in both the direct/inverse design methods and the experimental validations, the accurate grasp of the sweep characteristic of the blade’s 3-D swept shock surface becomes more concerned than before. Associated with relevant blading variables, this paper studied in uniformity the forward and zero and backward sweeps of shock surfaces, defined and resolved every kind of useful sweep angle, obtained dimensionless sweep similarity factors, suggested a kind of method for the quantitative classification of 3-D shock structures, proposed the principle of 3-D shock structure measurements. Two rotor blade leading edge shock surfaces from two high loading single stage fans are analysed and contrasted. This study is the foundation of the kinematic design of swept shock surfaces.
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Reports on the topic "Axial flow compressors. Compressors. Aerodynamics"

1

Liaw, Der-Cherng, Raymond A. Adomaitis, and Eyad H. Abed. Nonlinear Dynamics of Axial Flow Compressors: A Parametric Study. Fort Belvoir, VA: Defense Technical Information Center, March 1991. http://dx.doi.org/10.21236/ada454865.

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2

Adomaitis, Raymond A., Der-Cherng Liaw, and Eyad H. Abed. Nonlinear Dynamics of Axial-Flow Compressors: A Parametric Study. Fort Belvoir, VA: Defense Technical Information Center, January 1992. http://dx.doi.org/10.21236/ada454959.

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