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  • AERODYNAMICS  (14)
  • AIRCRAFT PROPULSION AND POWER  (1)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (1)
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  • 11
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    Performance of a tandem-rotor/tandem-stator conical-flow compressor designed for a pressure ratio of 3 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A conical-flow compressor stage with a large radius change through the rotor was tested at three values of rotor tip clearance. The stage had a tandem rotor and a tandem stator. Peak efficiency at design speed was 0.774 at a pressure ratio of 2.613. The rotor was tested without the stator, and detailed survey data were obtained for each rotor blade row. Overall peak rotor efficiency was 0.871 at a pressure ratio of 2.952.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2034 , E-369 , NAS 1.60:2034 , AVRADCOM-TR-81-C-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Experimental performance of a 16.10-centimeter-tip-diameter sweptback centrifugal compressor designed for a 6:1 pressure ratio (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A backswept impeller with design mass flow rate of 1.033 kg/sec was tested with both a vaned diffuser and a vaneless diffuser to establish stage and impeller characteristics. Design stage pressure ratio of 5.9:1 was attained at a flow slightly lower than the design value. Flow range at design speed was 6 percent of choking flow. Impeller axial tip clearance at design speed was varied to determine effect on stage and impeller performance.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3552 , E-9074
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor flow field (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor (LSCC) flow field has been conducted using laser anemometry and Dawes' 3D viscous code. The experimental configuration consists of a backswept impeller followed by a vaneless diffuser. Measurements of the three-dimensional velocity field were acquired at several measurement planes through the compressor. The measurements describe both the throughflow and secondary velocity field along each measurement plane. In several cases the measurements provide details of the flow within the blade boundary layers. Insight into the complex flow physics within centrifugal compressors is provided by the computational analysis, and assessment of the CFD predictions is provided by comparison with the measurements. Five-hole probe and hot-wire surveys at the inlet and exit to the rotor as well as surface flow visualization along the impeller blade surfaces provide independent confirmation of the laser measurement technique.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 92-GT-213 , ; 17 p.|ASME, International Gas Turbine and Aeroengine Congress and Exposition; Jun 01, 1992 - Jun 04, 1992; Cologne; Germany
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Investigation of the three-dimensional flow field within a transonic fan rotor: Experiment and analysis (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation of the three dimensional flow field through a low aspect ratio, transonic, axial flow fan rotor has been conducted using an advanced laser anemometer (LA) system. Laser velocimeter measurements of the rotor flow field at the design operating speed and over a range of through flow conditions are compared to analytical solutions. The numerical technique used herein yields the solution to the full, three dimensional, unsteady Euler equations using an explicit time marching, finite volume approach. The numerical analysis, when coupled with a simplified boundary layer calculation, generally yields good agreement with the experimental data. The test rotor has an aspect ratio of 1.56, a design total pressure ratio of 1.629 and a tip relative Mach number of 1.38. The high spatial resolution of the LA data matrix (9 radial by 30 axial by 50 blade to blade) permits details of the transonic flow field such as shock location, turning distribution and blade loading levels to be investigated and compared to analytical results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83739 , E-2150 , NAS 1.15:83739 , USAAVSCOM-TR-83-C-16 , Ann. Intern. Gas Turbine Conf.; Jun 03, 1984 - Jun 07, 1984; Amsterdam; Netherlands
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    NASA TECHNICAL REPORTS
  • 15
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    Effect of area ratio on the performance of a 5.5:1 pressure ratio centrifugal impeller (1986)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A centrifugal impeller which was initially designed for a pressure ratio of approximately 5.5 and a mass flow rate of 0.959 kg/sec was tested with a vaneless diffuser for a range of design point impeller area ratios from 2.322 to 2.945. The impeller area ratio was changed by successively cutting back the impeller exit axial width from an initial value of 7.57 mm to a final value of 5.97 mm. In all, four separate area ratios were tested. For each area ratio a series of impeller exit axial clearances was also tested. Test results are based on impeller exit surveys of total pressure, total temperature, and flow angle at a radius 1.115 times the impeller exit radius. Results of the tests at design speed, peak efficiency, and an exit tip clearance of 8 percent of exit blade height show that the impeller equivalent pressure recovery coefficient peaked at a design point area ratio of approximately 2.748 while the impeller aerodynamic efficiency peaked at a lower value of area ratio of approximately 2.55. The variation of impeller efficiency with clearance showed expected trends with a loss of approximately 0.4 points in impeller efficiency for each percent increase in exit axial tip clearance for all impellers tested.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87237 , E-2190 , NAS 1.15:87237 , USAAVSCOM-TR-85-C-21 , TR-85-C-21 , International Gas Turbine Conference and Exhibition; Jun 08, 1986 - Jun 12, 1986; Dusseldorf; Germany
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    NASA TECHNICAL REPORTS
  • 16
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    NASA low-speed centrifugal compressor for 3-D viscous code assessment and fundamental flow physics research (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A low speed centrifugal compressor facility recently built by the NASA Lewis Research Center is described. The purpose of this facility is to obtain detailed flow field measurements for computational fluid dynamic code assessment and flow physics modeling in support of Army and NASA efforts to advance small gas turbine engine technology. The facility is heavily instrumented with pressure and temperature probes, both in the stationary and rotating frames of reference, and has provisions for flow visualization and laser velocimetry. The facility will accommodate rotational speeds to 2400 rpm and is rated at pressures to 1.25 atm. The initial compressor stage being tested is geometrically and dynamically representative of modern high-performance centrifugal compressor stages with the exception of Mach number levels. Preliminary experimental investigations of inlet and exit flow uniformly and measurement repeatability are presented. These results demonstrate the high quality of the data which may be expected from this facility. The significance of synergism between computational fluid dynamic analysis and experimentation throughout the development of the low speed centrifugal compressor facility is demonstrated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-103710 , E-5938 , NAS 1.15:103710 , AVSCOM-TR-91-C-003 , AD-A242473 , International Gas Turbine and Aeroengine Congress and Exposition; Jun 03, 1991 - Jun 06, 1991; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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