scholarly journals Discussion: “Casing Wall Boundary-Layer Development Through an Isolated Compressor Rotor” (Hunter, I. H., and Cumpsty, N. A., 1982, ASME J. Eng. Power, 104, pp. 805–817)

1982 ◽  
Vol 104 (4) ◽  
pp. 817-817
Author(s):  
L. H. Smith
Keyword(s):  
Boundary Layer ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Layer Development

Casing Wall Boundary-Layer Development Through an Isolated Compressor Rotor

1982 ◽  
Vol 104 (4) ◽  
pp. 805-817 ◽  
Author(s):  
I. H. Hunter ◽  
N. A. Cumpsty
Keyword(s):  
Boundary Layer ◽  
Large Scale ◽  
Outer Wall ◽  
Tip Clearance ◽  
Pressure Probe ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Layer Development

Detailed measurements were made of the casing wall boundary layer development across a large-scale, low-speed axial compressor rotor blade row. An important feature of the work was the use of blading which allowed the tip clearance to be varied. A conventional pressure probe was used to obtain time-averaged measurements of the outer-wall boundary layer downstream of the rotor whilst a hot-wire anenometry technique yielded the three-dimensional, blade to blade structure of the flow. The downstream boundary layer was found to thicken as the rotor loading and blade-end clearance were increased, with fluid tending to accumulate towards the pressure side of the passage. By its pronounced effects upon wall boundary layer development, tip clearance had a deleterious effect upon the performance of the compressor.

Laser-Doppler Velocimeter Measurement of Annulus Wall Boundary Layer Development in a Compressor Rotor

1988 ◽  
Vol 110 (3) ◽  
pp. 377-385 ◽  
Author(s):  
B. Lakshminarayana ◽  
K. N. S. Murthy
Keyword(s):  
Boundary Layer ◽  
Laser Doppler ◽  
Laser Doppler Velocimeter ◽  
Leakage Flow ◽  
Detailed Measurement ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Layer Development

Detailed measurement of the flow field in the tip region of a compressor rotor was carried out using a laser-Doppler velocimeter (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. In addition, the relative stagnation pressures were measured from a Kiel probe; static pressures were derived from this and from the LDV measurement. The data are interpreted to understand annulus-wall boundary layer development inside the rotor, leakage flow, and losses in the tip region. 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.

Wall Boundary Layer Development Near the Tip Region of an IGV of an Axial Flow Compressor

1984 ◽  
Vol 106 (2) ◽  
pp. 337-345
Author(s):  
B. Lakshminarayana ◽  
N. Sitaram
Keyword(s):  
Boundary Layer ◽  
Guide Vane ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Inlet Guide Vane ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Flow Compressor

The annulus wall boundary layer inside the blade passage of the inlet guide vane (IGV) passage of a low-speed axial compressor stage was measured with a miniature five-hole probe. The three-dimensional velocity and pressure fields were measured at various axial and tangential locations. Limiting streamline angles and static pressures were also measured on the casing of the IGV passage. Strong secondary vorticity was developed. The data were analyzed and correlated with the existing velocity profile correlations. The end wall losses were also derived from these data.

Investigation of the Tip Clearance Flow Inside and at the Exit of a Compressor Rotor Passage—Part I: Mean Velocity Field

1983 ◽  
Vol 105 (1) ◽  
pp. 1-12 ◽  
Author(s):  
A. Pandya ◽  
B. Lakshminarayana
Keyword(s):  
Boundary Layer ◽  
Tip Clearance ◽  
Mean Flow ◽  
Ensemble Averaging ◽  
Mean Velocity ◽  
Tip Clearance Flow ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Wall Boundary ◽  
Clearance Flow

This paper reports on an experimental study of the nature of the tip clearance flow in a moderately loaded compressor rotor. The measurements reported were obtained using a stationary two-sensor, hot-wire probe in combination with an ensemble averaging technique. The flow field was surveyed at various radial locations and at ten axial locations, four of which were inside the blade passage in the clearance region and the remaining six outside the passage. Variations of the mean flow properties in the tangential and the radial directions at various axial locations were derived from the data. Variation of leakage velocity at different axial stations and the annulus-wall boundary layer profiles from passage-averaged mean velocities were also estimated. The results indicate that there exists a region of strong interaction of the leakage flow with the annulus-wall boundary layer at half-chord. The profiles are well-behaved beyond this point. The rotor exit flow is found to be uniform beyond 3/4 blade chord downstream of the rotor trailing edge.

Three-Dimensional Flow Field in the Tip Region of a Compressor Rotor Passage—Part I: Mean Velocity Profiles and Annulus Wall Boundary Layer

1982 ◽  
Vol 104 (4) ◽  
pp. 760-771 ◽  
Author(s):  
B. Lakshminarayana ◽  
M. Pouagare ◽  
R. Davino
Keyword(s):  
Boundary Layer ◽  
Flow Field ◽  
Three Dimensional ◽  
Leading Edge ◽  
Leakage Flow ◽  
Suction Surface ◽  
Mean Velocity ◽  
Wall Boundary Layer ◽  
Compressor Rotor ◽  
Wall Boundary

The flow field in the annulus wall and tip region of a compressor rotor was measured using a triaxial, hot-wire probe rotating with the rotor. The flow was surveyed across the entire passage at five axial locations (leading edge, 1/4 chord, 1/2 chord, 3/4 chord, and trailing edge locations) and at six radial locations inside the passage. The data derived include all three components of mean velocity. Blade-to-blade variations of the velocity components, pitch and yaw angles, as well as the passage-averaged mean properties of the annulus wall boundary layer, are derived from this data. The measurements indicate that the leakage flow starts beyond a quarter-chord and tends to roll up farther away from the suction surface than that observed in cascades. Substantial velocity deficiencies and radial inward velocities are observed in this region. The annulus wall boundary layer is well behaved up to half a chord, beyond which interactions with the leakage flow produce complex profiles.

The Simulation of Axial Compressor Performance Using an Annulus Wall Boundary Layer Theory

1975 ◽  
Vol 97 (3) ◽  
pp. 305-317 ◽  
Author(s):  
T. F. Balsa ◽  
G. L. Mellor
Keyword(s):  
Boundary Layer ◽  
Boundary Layers ◽  
Axial Compressor ◽  
Boundary Layer Theory ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Compressor Performance ◽  
High Mach ◽  
Factor Skin

This paper summarizes the development of a computer program to simulate axial compressor performance. The program incorporates a well-established technique for cascade performance prediction and a modified radial equilibrium method of calculating the mainstream axial velocity distribution. The program’s most important feature is a new theory of annulus wall boundary layers which predicts annulus boundary layer development and losses. The empirical input to the present annulus wall boundary layer model is very restricted and involves well defined quantities: shape factor, skin friction, and leakage coefficients. Special provision is made for cases where the annulus wall boundary layers are merged; this aspect needs improvement however. Theoretically derivable losses due to the annulus wall, in combination with cascade losses, yield overall compressor efficiency. In the interest of being abstemious with empiricism, no attempt has been made to introduce high Mach number cascade loss corrections at this time and the values of the empirical parameters in the boundary layer theory are held fixed. Considering the very restricted empirical content of the model and the absence of adjustable parameters, the current predictions of compressor performance are quite good.

Assessing the Influence of Aerosol on Radiation and Its Roles in Planetary Boundary Layer Development

2021 ◽  
Vol 35 (2) ◽  
pp. 384-392
Author(s):  
Zhigang Cheng ◽  
Yubing Pan ◽  
Ju Li ◽  
Xingcan Jia ◽  
Xinyu Zhang ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Planetary Boundary Layer ◽  
Boundary Layer Development ◽  
Layer Development
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