Relevant bibliographies by topics / Gas flow in axial compressors

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  2. Dissertations / Theses
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Academic literature on the topic 'Gas flow in axial compressors'

Author: Grafiati
Published: 4 June 2021
Last updated: 3 February 2022

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Journal articles on the topic "Gas flow in axial compressors"

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Song, T. W., T. S. Kim, J. H. Kim, and S. T. Ro. "Performance prediction of axial flow compressors using stage characteristics and simultaneous calculation of interstage parameters." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 215, no. 1 (February 1, 2001): 89–98. http://dx.doi.org/10.1243/0957650011536598.

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A new method for predicting performance of multistage axial flow compressors is proposed that utilizes stage performance curves. The method differs from the conventional sequential stage-stacking method in that it employs simultaneous calculation of all interstage variables (temperature, pressure and flow velocity). A consistent functional formulation of governing equations enables this simultaneous calculation. The method is found to be effective, i.e. fast and stable, in obtaining solutions for compressor inlet and outlet boundary conditions encountered in gas turbine analyses. Another advantage of the method is that the effect of changing the angles of movable stator vanes on the compressor's operating behaviour can be simulated easily. Accordingly, the proposed method is very suitable for complicated gas turbine system analysis. This paper presents the methodology and performance estimation results for various multistage compressors employing both fixed and variable vane setting angles. The effect of interstage air bleeding on compressor performance is also demonstrated.
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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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Wisler, D. C., R. C. Bauer, and T. H. Okiishi. "Secondary Flow, Turbulent Diffusion, and Mixing in Axial-Flow Compressors." Journal of Turbomachinery 109, no. 4 (October 1, 1987): 455–69. http://dx.doi.org/10.1115/1.3262127.

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The relative importance of convection by secondary flows and diffusion by turbulence as mechanisms responsible for mixing in multistage, axial-flow compressors has been investigated by using the ethylene tracer-gas technique and hot-wire anemometry. The tests were conducted at two loading levels in a large, low-speed, four-stage compressor. The experimental results show that considerable cross-passage and spanwise fluid motion can occur and that both secondary flow and turbulent diffusion can play important roles in the mixing process, depending upon location in the compressor and loading level. In the so-called freestream region, turbulent diffusion appeared to be the dominant mixing mechanism. However, near the endwalls and along airfoil surfaces at both loading levels, the convective effects from secondary flow were of the same order of magnitude as, and in some cases greater than, the diffusive effects from turbulence. Calculations of the secondary flowfield and mixing coefficients support the experimental findings.
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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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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 (April 1, 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-dimensional analyses show the development of spanwise (radial) and circumferential flows in the stator and the change in location and extent of separated flow regions as loading increases. The numerical solutions support previous interpretations of experimental data obtained on the same blading using the ethylene tracer-gas technique and hot-wire anemometry. These results, plus new tracer-gas data, show that both secondary flow and turbulent diffusion are mechanisms responsible for both spanwise and circumferential mixing in axial-flow compressors. The relative importance of the two mechanisms depends upon the configuration and loading levels. It appears that using the correct spanwise distributions of time-averaged inlet boundary conditions for three-dimensional Navier–Stokes computations enables one to explain much of the flow physics for this stator.
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Sehra, A., J. Bettner, and A. Cohn. "Design of a High-Performance Axial Compressor for Utility Gas Turbine." Journal of Turbomachinery 114, no. 2 (April 1, 1992): 277–86. http://dx.doi.org/10.1115/1.2929141.

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An aerodynamic design study to configure a high-efficiency industrial-size gas turbine compressor is presented. This study was conducted using an advanced aircraft engine compressor design system. Starting with an initial configuration based on conventional design practice, compressor design parameters were progressively optimized. To improve the efficiency potential of this design further, several advanced design concepts (such as stator ends bends and velocity controlled airfoils) were introduced. The projected poly tropic efficiency of the final advanced concept compressor design having 19 axial stages was estimated at 92.8 percent, which is 2 to 3 percent higher than the current high-efficiency aircraft turbine engine compressors. The influence of variable geometry on the flow and efficiency (at design speed) was also investigated. Operation at 77 percent design flow with inlet guide vanes and front five variable stators is predicted to increase the compressor efficiency by 6 points as compared to conventional designs having only the inlet guide vane as variable geometry.
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Ehrich, F. "Rotor Whirl Forces Induced by the Tip Clearance Effect in Axial Flow Compressors." Journal of Vibration and Acoustics 115, no. 4 (October 1, 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” model to simulate the operation of a compressor rotor deflected radially in its clearance, it is possible to derive a quantitative estimate of the proportionality factor β which relates the Thomas/Alford force in axial flow compressors (i.e., the tangential force generated by a radial deflection of the rotor) to the torque level in the compressor. The analysis makes use of experimental data from the GE Aircraft Engines Low Speed Research Compressor facility comparing the performance of three different axial flow compressors, each with four stages (typical of a mid-block of an aircraft gas turbine compressor) at two different clearances (expressed as a percent of blade length)—CL/L = 1.4 percent and CL/L = 2.8 percent. It is found that the value of β is in the range of +0.27 to −0.71 in the vicinity of the stages’ nominal operating line and +0.08 to −1.25 in the vicinity of the stages’ operation at peak efficiency. The value of β reaches a level of between −1.16 and −3.36 as the compressor is operated near its stalled condition. The final result bears a very strong resemblance to the correlation obtained by improvising a normalization of the experimental data of Vance and Laudadio (1984) and a generic relationship to the analytic results of Colding-Jorgensen (1990).
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Cruz-Manzo, Samuel, Senthil Krishnababu, Vili Panov, and Chris Bingham. "Inter-Stage Dynamic Performance of an Axial Compressor of a Twin-Shaft Industrial Gas Turbine." Machines 8, no. 4 (December 9, 2020): 83. http://dx.doi.org/10.3390/machines8040083.

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In this study, the inter-stage dynamic performance of a multistage axial compressor is simulated through a semi-empirical model constructed in the Matlab Simulink environment. A semi-empirical 1-D compressor model developed in a previous study has been integrated with a 0-D twin-shaft gas turbine model developed in the Simulink environment. Inter-stage performance data generated through a high-fidelity design tool and based on throughflow analysis are considered for the development of the inter-stage modeling framework. Inter-stage performance data comprise pressure ratio at various speeds with nominal variable stator guide vane (VGV) positions and with hypothetical offsets to them with respect to the gas generator speed (GGS). Compressor discharge pressure, fuel flow demand, GGS and power turbine speed measured during the operation of a twin-shaft industrial gas turbine are considered for the dynamic model validation. The dynamic performance of the axial-compressor, simulated by the developed modeling framework, is represented on the overall compressor map and individual stage characteristic maps. The effect of extracting air through the bleed port in the engine center-casing on transient performance represented on overall compressor map and stage performance maps is also presented. In addition, the dynamic performance of the axial-compressor with an offset in VGV position is represented on the overall compressor map and individual stage characteristic maps. The study couples the fundamental principles of axial compressors and a semi-empirical modeling architecture in a complementary manner. The developed modeling framework can provide a deeper understanding of the factors that affect the dynamic performance of axial compressors.
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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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Sieverding, Frank, Beat Ribi, Michael Casey, and Michael Meyer. "Design of Industrial Axial Compressor Blade Sections for Optimal Range and Performance." Journal of Turbomachinery 126, no. 2 (April 1, 2004): 323–31. http://dx.doi.org/10.1115/1.1737782.

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Background: The blade sections of industrial axial flow compressors require a wider range from surge to choke than typical gas turbine compressors in order to meet the high volume flow range requirements of the plant in which they operate. While in the past conventional blade profiles (NACA65 or C4 profiles) at moderate Mach number have mostly been used, recent well-documented experience in axial compressor design for gas turbines suggests that peak efficiency improvements and considerable enlargement of volume flow range can be achieved by the use of so-called prescribed velocity distribution (PVD) or controlled diffusion (CD) airfoils. Method of approach: The method combines a parametric geometry definition method, a powerful blade-to-blade flow solver and an optimization technique (breeder genetic algorithm) with an appropriate fitness function. Particular effort has been devoted to the design of the fitness function for this application which includes non-dimensional terms related to the required performance at design and off-design operating points. It has been found that essential aspects of the design (such as the required flow turning, or mechanical constraints) should not be part of the fitness function, but need to be treated as so-called “killer” criteria in the genetic algorithm. Finally, it has been found worthwhile to examine the effect of the weighting factors of the fitness function to identify how these affect the performance of the sections. Results: The system has been tested on the design of a repeating stage for the middle stages of an industrial axial compressor. The resulting profiles show an increased operating range compared to an earlier design using NACA65 profiles. Conclusions: A design system for the blade sections of industrial axial compressors has been developed. Three-dimensional CFD simulations and experimental measurements demonstrate the effectiveness of the new profiles with respect to the operating range.
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Dissertations / Theses on the topic "Gas flow in axial compressors"

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McDougall, Neil Malcolm. "Stall inception in axial compressors." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.237803.

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Storer, John Andrew. "Tip clearance flow in axial compressors." Thesis, University of Cambridge, 1991. https://www.repository.cam.ac.uk/handle/1810/251503.

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Wilson, Alexander George. "Stall and surge in axial flow compressors." Thesis, Cranfield University, 1996. http://dspace.lib.cranfield.ac.uk/handle/1826/10432.

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The objective of the work described in this thesis is twofold; to elucidate the nature of stall and surge in an axial flow aeroengine compressor, and to improve on current computational stall modelling techniques. Particular attention is paid to the initial stages of the stall/surge transient, and to the possibility of using active control techniques to prevent or delay the onset of stall/surge. A detailed analysis is presented of measurements of the stalling behaviour of a Rolls- Royce VIPER jet engine, showing a wide variety of stall inception and post-stall behaviour. Stall transients are traced from disturbances through to stable rotating stall or axisymmetic surge. The stall inception pattern at nearly all speeds is shown to conform to the short circumferential length scale pattern described by Day [1993a]. A multiple compressors in parallel stall model is developed using conventional stall modelling techniques, but extended to include the effects of the jet engine environment The model is shown to give a good representation of the overall stalling behaviour of the engine, although the details of the stall inception period are not accurately predicted. A system identification technique is applied to the results of the model in order to develop a method of active control of stall/surge. A new stall model is introduced and developed, based on a time-accurate three dimensional (but pitchwise averaged) solution of the viscous flow equations, with bladerow performance represented by body forces. The flow in the annulus boundary layers is calculated directly, and hence this new method is sufficiently complex to model the initial localised disturbances that lead to stall/surge. At the same time the computational power required is compatible with application to long multistage compressors.
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Gallimore, Simon John. "Spanwise mixing in multi-stage axial compressors." Thesis, University of Cambridge, 1986. https://www.repository.cam.ac.uk/handle/1810/250879.

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McGlumphy, Jonathan. "Numerical Investigation of Subsonic Axial-Flow Tandem Airfoils for a Core Compressor Rotor." Diss., Virginia Tech, 2008. http://hdl.handle.net/10919/26039.

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The tandem airfoil has potential to do more work as a compressor blade than a single airfoil without incurring significantly higher losses. Although tandem blades are sometimes employed as stators, they have not been used in any known commercial rotors. The goal of this work is to evaluate the aerodynamic feasibility of using a tandem rotor in the rear stages of a core compressor. As such, the results are constrained to shock-free, fully turbulent flow. The work is divided into 2-D and 3-D simulations. The 3-D results are subject to an additional constraint: thick endwall boundary layers at the inlet. Existing literature data on tandem airfoils in 2-D rectilinear cascades have been compiled and presented in a Lieblein loss versus loading correlation. Large scatter in the data gave motivation to conduct an extensive 2-D CFD study evaluating the overall performance as a function of the relative positions of the forward and aft airfoils. CFD results were consistent with trends in the open literature, both of which indicate that a properly designed tandem airfoil can outperform a comparable single airfoil on- and off-design. The general agreement of the CFD and literature data serves as a validation for the computational approach. A high hub-to-tip ratio 3-D blade geometry was developed based upon the best-case tandem airfoil configuration from the 2-D study. The 3-D tandem rotor was simulated in isolation in order to scrutinize the fluid mechanisms of the rotor, which had not previously been well documented. A geometrically similar single blade rotor was also simulated under the same conditions for a baseline comparison. The tandem rotor was found to outperform its single blade counterpart by attaining a higher work coefficient, polytropic efficiency and numerical stall margin. An examination of the tandem rotor fluid mechanics revealed that the forward blade acts in a similar manner to a conventional rotor. The aft blade is strongly dependent upon the flow it receives from the forward blade, and tends to be more three-dimensional and non-uniform than the forward blade.
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Ozturk, Harun Kemal. "A computational study of flow and heat transfer in gas turbine axial compressor stator-wells." Thesis, University of Sussex, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.388675.

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Lyes, Peter A. "Low speed axial compressor design and evaluation : High speed representation and endwall flow control studies." Thesis, Cranfield University, 1999. http://hdl.handle.net/1826/4251.

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This Thesis reports the design, build and test of two sets of blading for the Cranfield University low speed research compressor. The first of these was a datum low speed design based on the fourth stage of the DERA high speed research compressor C 147. The emphasis of this datum design was on the high-to-low speed transformation process and the evaluation of such a process through comparing detailed flow measurements from both compressors. Area traverse measurements in both the stationary and rotating frame of reference were taken at Cranfield along with overall performance, blade surface static pressure and flow visualisation measurements. These compare favourably with traverse and performance measurements taken on C147 before commencement of the PhD work. They show that despite the compromises made during the transformation process, due to both geometric and aerodynamic considerations, both the primary and secondary flow features can be successfully reproduced in the low speed environment. The aim of the second design was to improve on the performance of the datum blading through the use of advanced '3D' design concepts such as lean and sweep. The blading used nominally the same blade sections as the datum, and parametric studies were conducted into various lean/sweep configurations to try to optimise the blade performance. The final blade geometry also incorporated leading edge recambering towards the fixed endwalls of both the rotor and stator. The '3D' blading demonstrated a 1.5% increase in efficiency (over the datum blading) at design flow rising to around 3% at near stall along with an improvement in stall margin and pressure rise characteristic. The design work was completed using the TRANSCode flow solver for both the blade-to-blade solutions (used in the SI-S2 datum design calculation) and the fully 3D solutions (for the advanced design and post datum design appraisal). The 3D solutions gave a reasonable representation of the mid-span and main 3D flow features but failed to model the corner and tip clearance flow accurately. An interesting feature of the low speed flowfield was the circumferential variation in total pressure observed at exit from all rotors for both designs. This was not present at high speed and represents one of the main differences between the high and low speed flow. Unsteady modelling of mid- height sections from the first stage indicate that part of this variation is due to the potential interaction of the rotor with the downstream stator while the remainder is due to the wake structure from the upstream stator convecting through the rotor passage. Finally, the implications for a high speed design based on the success of the 3D low speed design are considered.
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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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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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Seitz, Peter Alexander. "Casing treatment for axial flow compressors." Thesis, University of Cambridge, 1999. https://www.repository.cam.ac.uk/handle/1810/251677.

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Books on the topic "Gas flow in axial compressors"

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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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Wilde, Geoffrey. Flow matching of the stages of axial compressors. Derby: Rolls-Royce Heritage Trust, 1999.

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Design of highly loaded axial-flow fans and compressors. White River Junction, Vt: Concepts ETI, 2000.

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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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Steinke, Ronald J. Design of 9.271-pressure-ratio five-stage core compressor and overall performance for first three stages. Cleveland, Ohio: Lewis Research Center, 1986.

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

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Wennerstrom, Arthur J. Low aspect ratio axial flow compressors: Why and what it means. Warrendale, PA: Society of Automotive Engineers, 1986.

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

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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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Book chapters on the topic "Gas flow in axial compressors"

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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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Sultanian, Bijay K. "Axial-Flow Gas Turbines." In Fluid Mechanics and Turbomachinery, 285–307. Boca Raton: CRC Press, 2021. http://dx.doi.org/10.1201/9781003053996-12.

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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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Sugawara, H., K. Kuwabara, S. Takemori, A. Wada, and K. Sasaki. "20-kW Fast-Axial-Flow CO2 Laser with High-Frequency Turboblowers." In Gas Flow and Chemical Lasers, 265–74. Berlin, Heidelberg: Springer Berlin Heidelberg, 1987. http://dx.doi.org/10.1007/978-3-642-71859-5_40.

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Machon, V., C. M. McFarlane, and A. W. Nienow. "Power Input and Gas Hold up in Gas Liquid Dispersions Agitated by Axial Flow Impellers." In Fluid Mechanics and Its Applications, 91–98. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-015-7973-5_11.

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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 "Gas flow in axial compressors"

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Adamczyk, John J. "Wake Mixing in Axial Flow Compressors." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-029.

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Over the years it has been speculated that the performance of multi-stage axial flow compressors is enhanced by the passage of a wake through a blade row prior to being mixed-out by viscous diffusion. The link between wake mixing and performance depends on the ability to recover the total pressure deficit of a wake by a reversible flow process. This paper shows that such a process exists, it is unsteady, and is associated with the kinematics of the wake vorticity field. The analysis shows that the benefits of wake total pressure recovery can be estimated from linear theory and quantified in terms of a volume integral involving the deterministic stress and the mean strain rate. In the limit of large reduced frequency the recovery process is shown to be a direct function of blade circulation. Results are presented which show that the recovery process can reduce the wake mixing loss by as much as seventy percent. Under certain circumstances this can lead to nearly a point improvement in stage efficiency, a nontrivial amount.
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Day, I. J. "Stall Inception in Axial Flow Compressors." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-086.

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Studies have been conducted on two laboratory test compressors to investigate the process leading to the formation of finite amplitude rotating stall cells. The measurements were obtained from circumferential arrays of hot-wires and were spatially and temporarily analysed to show that modal perturbations are not always present prior to stall, and when present, sometimes have little direct effect on the formation of the stall cells. The measurements lead to the conclusion that the occurrence of modal perturbations, and the formation of finite amplitude stall cells, are two separate phenomena; both occurring under roughly the same conditions at the peak of the pressure rise characteristic. The measurements also underline the hitherto unsuspected importance of short length scale disturbances in the process of stall inception. Examples are given of different ways in which stall cells can develop and the conclusions are backed up with a summary of current test data from various machines around the world.
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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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4

Wellborn, Steven R., Ilya Tolchinsky, and Theodore H. Okiishi. "Modeling Shrouded Stator Cavity Flows in Axial-Flow Compressors." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-075.

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Experiments and computational analyses were completed to understand the nature of shrouded stator cavity flows. From this understanding, a one-dimensional model of the flow through shrouded stator cavities was developed. This model estimates the leakage massflow, temperature rise and angular momentum increase through the cavity, given geometry parameters and the flow conditions at the interface between the cavity and primary flow path. This cavity model consists of two components, one which estimates the flow characteristics through the labyrinth seals and the other which predicts the transfer of momentum due to windage. A description of the one-dimensional model is given. The incorporation and use of the one-dimensional model in a multistage compressor primary flow analysis tool is described. The combination of this model and the primary flow solver was used to reliably simulate the significant impact on performance of the increase of hub seal leakage in a twelve stage axial-flow compressor. Observed higher temperatures of the hub region fluid, different stage matching and lower overall efficiencies and core flow than expected could be correctly linked to increased hub seal clearance with this new technique. The importance of including these leakage flows in compressor simulations is shown.
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Liu, J., Z. C. Zhang, and D. J. Ye. "Flow Field Diagnosis in Multistage Axial Compressors." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-170.

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A mathematical model is developed for the flow field diagnosis problem in multistage axial compressors. In view of the ill-posedness of the diagnostic problem, an effective measure is adopted to transfer the diagnostic problem into a variational problem which is solved by a regularization method. Two numerical results demonstrate the rationality of the flow field diagnosis problem for the compressors running near the design point and the effectiveness of the computational method.
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Longley, J. P., and T. P. Hynes. "Stability of Flow Through Multistage Axial Compressors." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-311.

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This paper describes measurements of the performance of a research stage operating in isolation and as part of a multistage compressor. It is shown that the stall point and the stalled performance of the stage are properties of the system in which it operates rather than a property of the stage itself. The consequences of this for the estimation of the stall point for compressors and compression systems are discussed. The support that the measurements give to assumptions made by mathematical models which use the concept of an ‘underlying axisymmetric’ characteristic are highlighted.
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Khalid, S. Arif, Amrit S. Khalsa, Ian A. Waitz, Choon S. Tan, Edward M. Greitzer, Nicholas A. Cumpsty, John J. Adamczyk, and Frank E. Marble. "Endwall Blockage in Axial Compressors." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-188.

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This paper presents a new methodology for quantifying compressor endwall blockage and an approach, using this quantification, for defining the links between design parameters, flow conditions, and the growth of blockage due to tip clearance flow. Numerical simulations, measurements in a low speed compressor, and measurements in a wind tunnel designed to simulate a compressor clearance flow are used to assess the approach. The analysis thus developed allows predictions of endwall blockage associated with variations in tip clearance, blade stagger angle, inlet boundary layer thickness, loading level, loading profile, solidity and clearance jet total pressure. The estimates provided by this simplified method capture the trends in blockage with changes in design parameters to within 10%. More importantly, however, the method provides physical insight into, and thus guidance for control of, the flow features and phenomena responsible for compressor endwall blockage generation.
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McDougall, N. M., N. A. Cumpsty, and T. P. Hynes. "Stall Inception in Axial Compressors." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-63.

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Detailed measurements have been made of the transient stalling process in an axial compressor stage. The stage is of high hub-casing ratio and stall is initiated in the rotor. If the rotor tip clearance is small stall inception occurs at the hub, but at clearances typical for a multistage compressor the inception is at the tip. The crucial quantity in both cases is the blockage caused by the endwall boundary layer. Prior to stall disturbances rotate around the inlet flow in sympathy with rotating variations in the endwall blockage; these can persist for some time prior to stall, rising and falling in amplitude before the final increase which occurs as the compressor stalls.
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9

Escuret, J. F., and R. L. Elder. "Active Control of Surge in Multi-Stage Axial-Flow Compressors." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-039.

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This paper deals with a theoretical study of the active control of purely axial 1D instabilities in multi-stage axial-flow compressors. The paper briefly considers the development of a suitable surge model and continues with the derivation of a controller using linear optimal control theory. The controller is specifically designed to suppress the instabilities predicted by the linearised form of the surge model. The control technique involves a bleed being dynamically varied in response to fluctuations of variables. It is found that a stabilising optimal controller can always be obtained. The second part of the paper presents a non-linear simulation of the surge prediction model with the linear controller, using a 4th order Runge-Kutta scheme. This demonstrates how some non-linearities in the flow model can affect the controller operation. It is also shown that, the amplitudes and the frequency response required of the actuator to retain stability can exceed the practical limitations.
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Tang, Guo-Cai, Bing Hu, and Hui-Ming Zhang. "An Investigation of the Dynamic Characteristic of Axial Flow 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-210.

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This paper reports an experimental investigation of the dynamic behaviour of an axial flow compressor when the flow rate is forced to vary quickly. The results are discussed in two aspects: general trends and special points. Generally, there is a deviation of the dynamic characteristic from the steady–state one, depending upon the algebraic sum of the inertial effect and the lag effect. For the present axial flow compressor, lightly–loaded, the dynamic characteristic goes above the steady–state one while closing the valve and below the steady–state one for opening the valve. Physical explanation is given to the general trend and also to the difference between the behavior of the axial flow compressor and that of the centrifugal compressor. Specially, the rapid closing of the valve will end up with an operating point end dynamic breaking into the instability limit while the throttle setting is somewhat away from the instability limit position for steady–state operation; and the rapid opening of the valve may produce an initial transient decrease in flow rate thus may have an initial dynamic breaking into the instability limit. Physical explanation is also given to these two special points, which are of great engineering interest with regard to the instability issue.
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Reports on the topic "Gas flow in axial compressors"

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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