An Investigation Of The Rotor Wake Characteristics Of An Axial Flow Compressor With Clean And Distorted Inlet Flows
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Experimental Investigation of a Transonic Axial-flow-compressor Rotor with Double-circular-arc Airfoil Blade Sections
Author | : George W. Lewis (Jr.) |
Publisher | : |
Total Pages | : 32 |
Release | : 1954 |
Genre | : Axial flow compressors |
ISBN | : |
A Comparison of Predicted and Measured Inlet Distortion Flows in a Subsonic Axial Inlet Flow Compressor Rotor
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 200 |
Release | : 2018-07-17 |
Genre | : |
ISBN | : 9781722892371 |
Detailed flow measurements were taken inside an isolated axial compressor rotor operating subsonically near peak efficiency. These Laser Anemometer measurements were made with two inlet velocity profiles. One profile consisted of an unmodified baseline flow, and the second profile was distorted by placing axisymmetric screens on the hub and shroud well upstream of the rotor. A detailed comparison in the rotor relative reference frame between a Navier-Stokes solver and the measured experimental results showed good agreement between the predicted and measured flows. A primary flow is defined in the rotor and deviations and the computed predictions is made to assess the development of a passage vortex due to the distortion of the inlet flow. Computer predictions indicate that a distorted inlet profile has a minimal effect on the development of the flow in the rotor passage and the resulting passage vortex. Owen, Albert K. Glenn Research Center AXIAL FLOW; FLOW DISTRIBUTION; FLOW VELOCITY; INLET FLOW; SUBSONIC FLOW; TURBOCOMPRESSORS; VELOCITY DISTRIBUTION; COMPRESSOR ROTORS; COMPUTATIONAL FLUID DYNAMICS; FLOW DISTORTION; LASER ANEMOMETERS; NAVIER-STOKES EQUATION; SHROUDS; VORTICES...
Asymmetric Inlet Flows Throught Axial Compressors
Author | : Choon Sooi Tan |
Publisher | : |
Total Pages | : 134 |
Release | : 1980 |
Genre | : Aircraft gas-turbines |
ISBN | : |
A Comparison of Predicted and Measured Inlet Distortion Flows in a Subsonic Axial Inlet Flow Compressor Rotor
Author | : National Aeronautics and Space Adm Nasa |
Publisher | : |
Total Pages | : 200 |
Release | : 2020-04-09 |
Genre | : |
ISBN | : 9781790377749 |
Detailed flow measurements were taken inside an isolated axial compressor rotor operating subsonically near peak efficiency. These Laser Anemometer measurements were made with two inlet velocity profiles. One profile consisted of an unmodified baseline flow, and the second profile was distorted by placing axisymmetric screens on the hub and shroud well upstream of the rotor. A detailed comparison in the rotor relative reference frame between a Navier-Stokes solver and the measured experimental results showed good agreement between the predicted and measured flows. A primary flow is defined in the rotor and deviations and the computed predictions is made to assess the development of a passage vortex due to the distortion of the inlet flow. Computer predictions indicate that a distorted inlet profile has a minimal effect on the development of the flow in the rotor passage and the resulting passage vortex. Owen, Albert K. Glenn Research Center AXIAL FLOW; FLOW DISTRIBUTION; FLOW VELOCITY; INLET FLOW; SUBSONIC FLOW; TURBOCOMPRESSORS; VELOCITY DISTRIBUTION; COMPRESSOR ROTORS; COMPUTATIONAL FLUID DYNAMICS; FLOW DISTORTION; LASER ANEMOMETERS; NAVIER-STOKES EQUATION; SHROUDS; VORTICES...
British Reports, Translations and Theses
Author | : British Library. Lending Division |
Publisher | : |
Total Pages | : 444 |
Release | : 1984 |
Genre | : Great Britain |
ISBN | : |
Issue for Mar. 1981 contains index for Jan.-Mar. 1981 in microfiche form.
Investigation of an Impulse Axial-flow Compressor
Author | : John R. Erwin |
Publisher | : |
Total Pages | : 56 |
Release | : 1950 |
Genre | : Axial flow compressors |
ISBN | : |
Effects of a Rotating Aerodynamic Probe on the Flow Field of a Compressor Rotor
Author | : National Aeronautics and Space Adm Nasa |
Publisher | : Independently Published |
Total Pages | : 28 |
Release | : 2019-01-13 |
Genre | : Science |
ISBN | : 9781793904997 |
An investigation of distortions of the rotor exit flow field caused by an aerodynamic probe mounted in the rotor is described in this paper. A rotor total pressure Kiel probe, mounted on the rotor hub and extending up to the mid-span radius of a rotor blade channel, generates a wake that forms additional flow blockage. Three types of high-response aerodynamic probes were used to investigate the distorted flow field behind the rotor. These probes were: a split-fiber thermo-anemometric probe to measure velocity and flow direction, a total pressure probe, and a disk probe for in-flow static pressure measurement. The signals acquired from these high-response probes were reduced using an ensemble averaging method based on a once per rotor revolution signal. The rotor ensemble averages were combined to construct contour plots for each rotor channel of the rotor tested. In order to quantify the rotor probe effects, the contour plots for each individual rotor blade passage were averaged into a single value. The distribution of these average values along the rotor circumference is a measure of changes in the rotor exit flow field due to the presence of a probe in the rotor. These distributions were generated for axial flow velocity and for static pressure. Lepicovsky, Jan Glenn Research Center NNC06BA07B; 561581.02.08.03.21.02