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  • 1
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    NASA low-speed centrifugal compressor for 3-D viscous code assessment and fundamental flow physics research (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    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: ASME PAPER 91-GT-140
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of area ratio on the performance of a 5.5:1 pressure ratio centrifugal impeller (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    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: ASME PAPER 86-GT-303
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Improved method for calculating transonic velocities on blade-to-blade stream surfaces of a turbomachine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method was developed to improve the accuracy of an existing computer program used to calculate transonic velocities on a blade-to-blade surface of a turbomachine. The method eliminates problems encountered in obtaining solutions with the velocity gradient equation when large gradients in velocity occur through the blade row. With the improved method, results indicate that the transonic solution can be obtained by scaling the velocities obtained at the reduced mass flow rate where all velocities are subsonic thereby eliminating the need for a solution of the velocity gradient equation. Solutions obtained with the scaling method on a two dimensional compressor cascade and an axial turbine stator show good agreement with experimental data. The results obtained for the stationary blade rows and comparison of analytical results obtained with and without the present method suggest that the method will yield an improved solution for centrifugal compressor impellers.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1772 , E-128
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental performance of a 13.65-centimeter-tip-diameter tandem-bladed sweptback centrifugal compressor designed for a pressure ratio of 6 (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 13.65 cm tip diameter backswept centrifugal impeller having a tandem inducer and a design mass flow rate of 0.907 kg/sec was experimentally investigated to establish stage and impeller characteristics. Tests were conducted with both a cascade diffuser and a vaneless diffuser. A pressure ratio of 5.9 was obtained near surge for the smallest clearance tested. Flow range at design speed was 6.3 percent for the smallest clearance test. Impeller exit to shroud axial clearance at design speed was varied to determine the effect on stage and impeller performance.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1091
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Input generator for Denton 3-dimensional turbomachine-blade-row analysis code (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A users manual is presented for a computer program that prepares the bulk of the input data set required for the Denton three dimensional turbomachine blade row analysis code. The Denton input is generated from a minimum of geometry and flow variable information by using cubic spline curve fitting procedures. The features of the program are discussed. The input is described and special instructions are included to assist in its preparation. Sample input and output are included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83324 , E-1565 , NAS 1.15:83324
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental and computational results from a large low-speed centrifugal impeller (1993)
    In:  CASI
    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 and in several cases provide details of the flow within the blade boundary layers. The experimental and computational results provide a clear understanding of the development of the throughflow momentum wake which is characteristic of centrifugal compressors.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106421 , E-8258 , NAS 1.15:106421 , ARL-TR-331 , eeting of the AGARD Propulsion and Energetics Panel, Technology Requirements for Small Gas Turbine Engines; Oct 04, 1993 - Oct 06, 1993; Montreal, Ontario; Canada
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    NASA TECHNICAL REPORTS
  • 7
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    NASA Low-Speed Centrifugal Compressor for Fundamental Research (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A centrifugal compressor facility being built by the NASA Lewis Research Center is described; its purpose is to obtain benchmark experimental data for internal flow code verification and modeling. The facility will be heavily instrumented with standard pressure and temperature probes and have provisions for flow visualization and laser Doppler velocimetry. The facility will accommodate rotational speeds to 2400 rpm and will be rated at pressures to 1.25 atm. The initial compressor stage for testing is geometrically and dynamically representative of modern high-performance stages with the exception of Mach number levels. Design exit tip speed for the initial stage is 500 ft/sec with a pressure ratio of 1.17. The rotor exit backsweep is 55 deg from radial.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83398 , E-1675 , NAS 1.15:83398 , Joint Propulsion Conf. and Tech. Display; Jun 27, 1983 - Jun 29, 1983; Seattle
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    NASA TECHNICAL REPORTS
  • 8
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    Investigation of the three-dimensional flow field within a transonic fan rotor - Experiment and analysis (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    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 throughflow 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 x 30 axial x 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: ASME PAPER 84-GT-200
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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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
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    NASA TECHNICAL REPORTS
  • 10
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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
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