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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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    NASA TECHNICAL REPORTS
  • 2
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    Experimental and computational results from a large low-speed centrifugal impeller (1994)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: An experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor (LSCC) flow field was conducted using laser anemometry and Dawes' 3D viscous code. The experimental configuration consists of a back-swept 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: AIRCRAFT PROPULSION AND POWER
    Type: AGARD, Technology Requirements for Small Gas Turbines; 11 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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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
  • 4
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    Measurements of the unsteady flow field within the stator row of a transonic axial-flow fan. Part 2: Results and discussion (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Unsteady velocity field measurements made within the stator row of a transonic axial-flow fan are presented. Measurements were obtained at midspan for two different stator blade rows using a laser anemometer. The first stator row consists of double circular-arc airfoils with a solidity of 1.68. The second features controlled-diffusion airfoils with a solidity of 0.85. Both were tested at design-speed peak efficiency conditions. In addition, the controlled-diffusion stator was also tested at near stall conditions. The procedures developed here are used to identify the rotor wake generated and unresolved unsteadiness from the velocity measurements (rotor wake generated unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and unresolved unsteadiness refers to all remaining unsteadiness which contributes to the spread in the distribution of velocities such as vortex shedding, turbulence, etc.). Auto and cross correlations of these unsteady velocity fluctuations are presented to show their relative magnitude and spatial distributions. Amplification and attenuation of both rotor wake generated and unresolved unsteadiness are shown to occur within the stator blade passage.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88946 , E-3394 , NAS 1.15:88946 , USAAVSCOM-TR-86-C-31
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Measurements of the unsteady flow field within the stator row of a transonic axial-flow fan. 1: Measurement and analysis technique (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This two-part paper presents laser anemometer measurements of the unsteady velocity field within the stator row of a transonic axial-flow fan. The objective is to provide additional insight into unsteady blade-row interactions within high speed compressors which affect stage efficiency, energy transfer, and other design considerations. Part 1 describes the measurement and analysis techniques used for resolving the unsteady flow field features. The ensemble-average and variance of the measured velocities are used to identify the rotor wake generated and unresolved unsteadiness, respectively. (Rotor wake generated unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and the term unresolved unsteadiness refers to all remaining contributions to unsteadiness such as vortex shedding, turbulence, mass flow fluctuations, etc.). A procedure for calculating auto and cross correlations of the rotor wake generated and unresolved unsteady velocity fluctuations is described. These unsteady-velocity correlations have significance since they also result from a decomposition of the Navier-Stokes equations. This decomposition of the Navier-Stokes equations resulting in the velocity correlations used to describe the unsteady velocity field will also be outlined in this paper.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88945 , E-3393 , NAS 1.15:88945 , USAAVSCOM-TR-86-C-30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Measurements of the unsteady flow field within the stator row of a transonic axial-flow fan. II - Results and discussion (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Unsteady velocity field measurements made within the stator row of a transonic axial-flow fan are presented. Measurements were obtained at midspan for two different stator blade rows using a laser anemometer. The first stator row consists of double circular-arc airfoils with a solidity of 1.68. The second features controlled-diffusion airfoils with a solidity of 0.85. Both were tested at design-speed peak efficiency conditions. In addition, the controlled-diffusion stator was also tested at near stall conditions. The procedures developed here are used to identify the rotor wake generated and unresolved unsteadiness from the velocity measurements (rotor wake generated unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and unresolved unsteadiness refers to all remaining unsteadiness which contributes to the spread in the distribution of velocities such as vortex shedding, turbulence, etc.). Auto and cross correlations of these unsteady velocity fluctuations are presented to show their relative magnitude and spatial distributions. Amplification and attenuation of both rotor wake generated and unresolved unsteadiness are shown to occur within the stator blade passage.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 87-GT-227
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Measurements of the unsteady flow field within the stator row of a transonic axial-flow fan. I - Measurement and analysis technique (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This two-part paper presents laser anemometer measurements of the unsteady velocity field within the stator row of a transonic axial-flow fan. The objective is to provide additional insight into unsteady blade-row interactions within highspeed compressors which affect stage efficiency, energy transfer, and other design considerations. Part 1 describes the measurement and analysis techniques used for resolving the unsteady flow field features. The ensemble-average and variance of the measured velocities are used to identify the rotor wake generated and unresolved unsteadiness, respectively. (Rotor wake generated unsteadiness refers to the unsteadiness generated by the rotor wake velocity deficit and the term unresolved unsteadiness refers to all remaining contributions to unsteadiness such as vortex shedding, turbulence, mass flow fluctutions, etc.). A procedure for calculating auto and cross correlations of the rotor wake generated and unresolved unsteady velocity fluctuations is described. These unsteady-velocity correlations have significance since they also result from a decomposition of the Navier-Stokes equations. This decomposition of the Navier-Stokes equations resulting in the velocity correlations used to describe the unsteady velocity field will also be outlined in this paper.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 87-GT-226
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Rotor wake characteristics of a transonic axial flow fan (1985)
    In:  Other Sources
    Details
    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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    NASA TECHNICAL REPORTS
  • 9
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    A note on blade wake interaction influence on compressor stator row aerodynamic performance (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Attention is given to the effect of blade wake interactions on the performance of an axial flow compressor's stator row, for the case of compressor and fan stator flows without shocks. The measured midspan loss of total pressure can be related to stator surface boundary layers, the chopped rotor wakes passing through the stator row, and the interaction between these flows. The interaction between rotor blade wake segments and stator blade surface boundary layers generates much higher losses than expected in both the stator wake and in the region of flow between stator boundary layers/wakes, if interaction effects are ignored.
    Keywords: AERODYNAMICS
    Type: ASME, Transactions, Journal of Engineering for Gas Turbines and Power (ISSN 0022-0825); 107; 549-551
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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