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  • 1
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    Rotor wake characteristics of a transonic axial-flow fan (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 24; 1802-181
    Format: text
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  • 2
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    Vortex shedding in high-speed compressor blade wakes (1988)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The wakes of highly loaded compressor blades are generally considered to be turbulent flows. Recent work has suggested that the blade wakes are dominated by a vortex streetlike structure. The experimental evidence supporting the wake vortex structure is reviewed. This structure is shown to redistribute thermal energy within the flowfield. The effect of the wake structure on conventional aerodynamic measurements of compressor performance is noted. A two-dimensional, time-accurate, viscous numerical simulation of the flow exhibits both vortex shedding in the wake and a lower-frequency flow instability that modulates the shedding. The numerical results are shown to agree quite well with the measurement from transonic compressor rotors.
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 4; 236-244
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  • 3
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    Active suppression of compressor instabilities (1986)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A strategy is proposed for controlling aerodynamic instabilities which limit the useful range of both axial and centrifugal turbomachines. Both local and global instabilities (incipient rotating stall and surge) are analyzed. A theory is developed which shows how an additional disturbance, driven from real time data measured within the machine, can be generated so as to realize a device with characteristics fundamentally different from those of the turbomachine without control; for the particular compressor analyzed, the control led to a 20 percent increase in the extent of the stable operating range. The use of structural dynamics to enhance stability is also discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1914
    Format: text
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  • 4
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    Rotor wake characteristics of a transonic axial flow fan (1985)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: State of the art turbomachinery flow analysis codes are not capable of predicting the viscous flow features within turbomachinery blade wakes. Until efficient 3D viscous flow analysis codes become a reality there is therefore a need for models which can describe the generation and transport of blade wakes and the mixing process within the wake. To address the need for experimental data to support the development of such models, high response pressure measurements and laser anemometer velocity measurements have been obtained in the wake of a transonic axial flow fan rotor.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1133
    Format: text
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  • 5
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    Quantitative density visualization in a transonic compressor rotor (1977)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The flow in a 59-cm-diameter high-work transonic compressor rotor has been visualized using a fluorescent gas, 2,3, butanedione, as a tracer. The technique allows the three-dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps were obtained by correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. These images and maps were used to analyze the three-dimensional nature of the blade's boundary layer and shock system.
    Keywords: AERODYNAMICS
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  • 6
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    Time resolved measurements in a low aspect ratio transonic compressor stage (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The time resolved flowfield in a low aspect ratio transonic compressor stage has been studied using a high frequency response sphere probe with a bandpass of D.C. to 20 kHz in a blowdown compressor facility. Averaged over the compressor annulus, the data agree well with those measured with standard pitot type probes on the same stage in a conventional test rig. Not all the spanwise distributions agree, however. These differences are explained as errors in the pitot probe readings due to fluctuations in the flow. The experimental data are compared to the results of a three-dimensional inviscid Euler calculation.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 82-GT-201 , International Gas Turbine Conference and Exhibit; Apr 18, 1982 - Apr 22, 1982; London
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  • 7
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    A comparison of the computed and experimental three dimensional flow in a transonic compressor rotor (1976)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The three dimensional inviscid flow in a transonic compressor rotor; total pressure ratio of 1.65, has been numerically computed using MacCormack's time-marching method. This solution is compared to intra-blade static density measurements obtained by gas fluorescence. These results and comparisons illustrate the importance of three dimensional flow phenomena in determining the rotor flow field and show that while the viscous phenomena have an important influence, particularly on the outflow, the inviscid computation properly models the flow in the inlet portion of the rotor passages.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-368 , Fluid and Plasma Dynamics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
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  • 8
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    Quantitative density visualization in a transonic rotor (1975)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The flow in a two foot diameter transonic rotor has been visualized using a fluorescent gas, 2, 3 butanedione, as a tracer. The technique allows the three dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps can be obtained after correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. The visualized flow is compared to data taken simultaneously by high frequency pressure transducers near the rotor entrance and exit planes.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-24 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
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  • 9
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    Shock structure in transonic compressor rotors (1979)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The inadequacy of axisymmetric theory in modeling the structure of the shock system in a transonic compressor rotor is shown with a simple model. A more accurate model for the flow near the sonic radius is proposed, which is supported by some flow visualization data and three-dimensional computations.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 17; Apr. 197
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  • 10
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    Active suppression of aerodynamic instabilities in turbomachines (1989)
    In:  Other Sources
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    Publication Date: 2019-07-12
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 204-211
    Format: text
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