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  • 1
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    Annulus wall boundary layer development in a compressor stage, including the effects of tip clearance (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The end-wall boundary layer development in a compressor stage, including the inlet guide vane (IGV) passage and the rotor passage, was measured. The measurement upstream of the rotor and inside the IGV passage were carried out with a five-hole probe. The data (blade-to-blade) inside the IGV passage were carried out with a five-hole probe. The data (blade-to-blade) inside the rotor passage were measured using a three-sensor rotating hot-wire below the tip clearance region and "V' configuration probe inside the clearance region. The rotor exit measurements (blade-to-blade) were acquired with a laser Doppler velocimeter. The velocity profiles and the integral properties are presented and interpreted. The boundary layer is comparatively well behaved up to the leading edge of the rotor, beyond which complex interactions result in very unconventional profiles. The momentum thicknesses decrease in the leakage flow region of the rotor. The momentum thicknesses and the limiting streamline angles predicted from a momentum integral technique agree well with the data up to the leading edge of the rotor.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Viscous Effects in Turbomachines; 17 p
    Format: text
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  • 2
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    Computation of three-dimensional viscous flows using a space-marching method (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A space-marching method, developed to compute three-dimensional flows for internal geometries, has been utilized to predict viscous flows through a curved duct and over a swept wing. The Navier-Stokes equations have been posed as an initial value problem by neglecting the streamwise viscous diffusion terms and by treating the pressure gradient as a known source term. The resulting equations have been solved by a non-iterative (single pass) algorithm at each streamwise step. The results are compared with earlier computations (based on iterative methods) and the experimental data. The agreement between the present predictions, the experimental data, and the earlier predictions is good for the cases computed. The computation time is only a fraction of the iterative methods.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1298
    Format: text
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  • 3
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    Laser Doppler velocimeter measurement of annulus wall boundary layer development in a compressor rotor (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Detailed measurement of the flow field in the tip region of a compressor rotor was carried out using LDV. The axial and tangential components of relative velocities were measured upstream, inside the passage, and at the exit of the rotor, up to about 20 percent of the blade span from the blade tip. The annulus-wall boundary layer is well behaved at the leading edge and far downstream of the rotor. But inside the passage, complex interactions between the leakage flow and the annulus-wall boundary layer result in unconventional profiles with wide deviations from models employed for analyses.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME PAPER 87-GT-251
    Format: text
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  • 4
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    Computation of three-dimensional viscous flows using a space-marching method (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 311-317
    Format: text
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  • 5
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    An experimental study on the effects of tip clearance on flow field and losses in an axial flow compressor rotor (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Detailed measurement of the flow field in the tip region of a compressor rotor was carried out using a Laser Doppler Velocimeter (LDV) and a Kiel probe at two different tip clearance heights. At both clearance sizes, the relative stagnation pressure and the axial and tangential components of relative velocities were measured upstream, inside the passage and downstream of the rotor, up to about 20 percent of the blade span from the annulus wall. The velocities, outlet angles, losses, momentum thickness, and force defect thickness are compared for the two clearances. A detailed interpretation of the effect of tip clearance on the flow field is given. There are substantial differences in flow field, on momentum thickness, and performance as the clearance is varied. The losses increase linearly within the passage and their values increase in direct proportion to tip clearance height. No discernable vortex (discrete) is observed downstream of the rotor.
    Keywords: AERODYNAMICS
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  • 6
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    Three dimensional flow field inside compressor rotor, including blade boundary layers (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flow in a turbomachinery blade passage has a predominant flow direction. The viscous diffusion in the streamwise direction is usually small and the elliptic influence is transmitted upstream through the pressure field. Starting with a guessed pressure field, it is possible to converge on the full elliptic solution by iterating between a parabolic solution and an iteration of the pressure field. The main steps of the calculation are given. The blade boundary layers which are three dimensional with laminar, transitional, turbulent, and separation zones are investigated. The kinetic energy is analyzed, and the dissipation equation is presented. Measurements were made of the three dimensional flow inside an axial flow compressor passage.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168410 , PSU/TURBO-82-1
    Format: application/pdf
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  • 7
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    Laser Doppler velocimeter measurement in the tip region of a compressor rotor (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The axial and tangential velocity components near the tip region of a compressor rotor were measured by a laser Doppler velocimeter. The measurements were taken at 25 radial locations in the outer twenty percent of the blade span and at 10 axial locations upstream, inside and at the exit of the rotor. The results are interpreted to derive the behavior of the leakage flow, annulus wall boundary layer growth, inviscid effects and the rotor wake decay characteristics in the tip region. The inviscid and annulus wall boundary layer effects dominate up to quarter chord, beyond which the leakage phenomena has a major influence in altering the flow characteristics in the outer ten percent of the blade span. The annulus wall boundary layer undergoes drastic change through the passage. The velocity field measured near the leading edge reveals the effects of rapid acceleration near the suction surface and the stagnation point on the pressure surface.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1602
    Format: text
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  • 8
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    Three-dimensional flowfield inside a low-speed axial flow compressor rotor (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 15, p. 2347, Accession no. A82-31964
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 21; 1679
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  • 9
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    Three dimensional flow field inside the passage of a low speed axial flow compressor rotor (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Measurements of the subsonic flow in the rotor passage of a single stage axial flow compressor were made to study the nature of the flow field and to verify the existing numerical codes. The velocity and pressure fields were measured across the entire rotor passage at six axial locations and at five radial locations. A five-hole probe, rotating with the rotor, was used to measure the three components of velocity, the static and the total pressure. The experimental results are compared with the predictions from Katsanis and McNally's computer program. The agreement between the two is good for most of the cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-1006 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
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  • 10
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    End wall flows in rotors and stators of a single stage compressor (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer code for solving the parabolized Navier-Stokes equations for internal flows was developed. Oscillations that develop in the calculation procedure are discussed. The measurements made in the hub and annulus wall boundary layers are summarized. The flow in the hub wall boundary layer, starting ahead of the inlet guide vanes to the inlet of the rotor is traced.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-169800 , NAS 1.26:169800 , PSU/TURBO-83-2
    Format: application/pdf
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