scholarly journals Closure to “Discussion of ‘Mean Velocity and Decay Characteristics of the Guidevane and Stator Blade Wake of an Axial Flow Compressor’” (1980, ASME J. Eng. Power, 102, p. 60)

1980 ◽  
Vol 102 (1) ◽  
pp. 60-60 ◽  
Author(s):  
B. Lakshminarayana ◽  
R. Davino
Keyword(s):  
Axial Flow ◽  
Mean Velocity ◽  
Axial Flow Compressor ◽  
Stator Blade ◽  
Flow Compressor

Mean Velocity and Decay Characteristics of the Guidevane and Stator Blade Wake of an Axial Flow Compressor

1980 ◽  
Vol 102 (1) ◽  
pp. 50-60 ◽  
Author(s):  
B. Lakshminarayana ◽  
R. Davino
Keyword(s):  
Axial Flow ◽  
Mean Velocity ◽  
Axial Flow Compressor ◽  
Profile Similarity ◽  
Blade Row ◽  
Wake Production ◽  
Flow Curvature ◽  
Stator Blade ◽  
Single Sensor ◽  
Flow Compressor

Pure tone noise, blade row vibrations, and aerodynamic losses are phenomena which are influenced by stator and IGV blade wake production, decay, and interaction in an axial-flow compressor. The objective of this investigation is to develop a better understanding of the nature of stator and IGV blade wakes that are influenced by the presence of centrifugal forces due to flow curvature. A single sensor hot wire probe was employed to determine the three mean velocity components of stator and IGV wakes of a single stage compressor. These wake profiles indicated a varying decay rate of the tangential and axial wake velocity components and a wake profile similarity. An analysis, which predicts this trend, has been developed. The radial velocities are found to be appreciable in both IGV and the stator wakes. This wake data as well as the data from other sources are correlated in this paper. Appreciable static pressure gradient across the wake is found to exist near the trailing edge of both stator and IGV.

Boundary-Layer Development on an Axial-Flow Compressor Stator Blade

1978 ◽  
Vol 100 (2) ◽  
pp. 287-292 ◽  
Author(s):  
R. L. Evans
Keyword(s):  
Boundary Layer ◽  
Axial Flow ◽  
Layer Growth ◽  
Ensemble Averaging ◽  
Mean Velocity ◽  
Axial Flow Compressor ◽  
Boundary Layer Development ◽  
Stator Blade ◽  
Flow Compressor ◽  
Layer Development

The boundary layer on an axial-flow compressor stator blade has been measured using an ensemble-averaging technique. Although the mean velocity profiles appear to indicate fully developed turbulent flow, ensemble-averaged instantaneous profiles show the boundary layer to be highly unsteady and transitional over much of the blade chord. At a given chordwise position, variations in boundary-layer thickness with time of up to 150 percent were recorded. When compared to boundary-layer development on a similar blade in a two-dimensional cascade the stator blade boundary-layer growth was found to be much greater. The results indicate that extreme caution should be used in attempting to predict blade boundary-layer development from cascade test results or steady calculation procedures.

The Manufacture of Glass Cloth/Resin Blades for an Axial Flow Compressor

1954 ◽  
Vol 58 (522) ◽  
pp. 434-434
Author(s):  
J. H. Horlock
Keyword(s):  
Polyester Resin ◽  
Axial Flow ◽  
Glass Cloth ◽  
Axial Flow Compressor ◽  
Stator Blade ◽  
Flow Compressor ◽  
The University

Glass Cloth/Polyester resin laminates similar to those described by Irving and Saunders (Journal, February 1954) have been used at the University Engineering Laboratory, Cambridge, in the manufacture of blades for an axial flow compressor. In the first experiments, an existing aluminium stator blade was used as a pattern, and a mould was made by pouring molten type metal round this pattern, held in a steel sided moulding box.

scholarly journals Experimental Investigation of the Flow Field in a Multistage Axial Flow Compressor

1996 ◽  
Vol 2 (4) ◽  
pp. 247-258 ◽  
Author(s):  
B. Lakshminarayana ◽  
N. Suryavamshi ◽  
J. Prato ◽  
R. Moritz
Keyword(s):  
Flow Field ◽  
Secondary Flow ◽  
Axial Flow ◽  
Suction Side ◽  
Mean Velocity ◽  
Axial Flow Compressor ◽  
Total Temperature ◽  
Single Sensor ◽  
Flow Compressor ◽  
Thermocouple Probe

The nature of the flow field in a three stage axial flow compressor, including a detailed survey at the exit of an embedded stator as well as the overall performance of the compressor is presented and interpreted in this paper. The measurements include area traverse of a miniature five hole probe (1.07 mm dia) downstream of stator 2, radial traverses of a miniature five hole probe at the inlet, downstream of stator 3 and at the exit of the compressor at various circumferential locations, area traverse of a low response thermocouple probe downstream of stator 2, radial traverses of a single sensor hot-wire probe at the inlet, and casing static pressure measurements at various circumferential and axial locations across the compressor at the peak efficiency operating point. Mean velocity, pressure and total temperature contours as well as secondary flow contours at the exit of the stator 2 are reported and interpreted. Secondary flow contours show the migration of fluid particles toward the core of the low pressure regions located near the suction side casing endwall corner.

Stator Endwall Leading-Edge Sweep and Hub Shroud Influence on Compressor Performance

1986 ◽  
Vol 108 (2) ◽  
pp. 224-232 ◽  
Author(s):  
D. L. Tweedt ◽  
T. H. Okiishi ◽  
M. D. Hathaway
Keyword(s):  
Axial Flow ◽  
Leading Edge ◽  
Outer Diameter ◽  
Loss Reduction ◽  
Local Loss ◽  
Axial Flow Compressor ◽  
Stator Blade ◽  
Inner Diameter ◽  
Compressor Performance ◽  
Flow Compressor

The use of stator endwall leading-edge sweep to improve axial-flow compressor stator row performance was examined experimentally. The aerodynamics of three stator hub (inner diameter) conditions, namely, a running clearance, a stationary clearance, and a shroud, were also investigated. Leading-edge sweep in the endwall regions of a stator blade can be beneficial in terms of loss reduction on the casing (outer diameter) end of a stator blade. It can also help at the hub end of a stator blade when either a stationary hub clearance or a hub shroud is used. A leading-edge sweep is detrimental (local loss increase) on the hub end of a stator blade when a running hub clearance is used. A running clearance is aerodynamically preferable to a stationary clearance.

Investigations on Stator Hub End Losses and its Control in an Axial Flow Compressor

2014 ◽  
Author(s):  
Kurian K. George ◽  
S. N. Agnimitra Sunkara ◽  
Jubin Tom George ◽  
Melvin Joseph ◽  
A. M. Pradeep ◽  
...  
Keyword(s):  
Experimental Studies ◽  
Axial Flow ◽  
Separated Flow ◽  
Tip Clearance ◽  
Axial Flow Compressor ◽  
Large Vortex ◽  
Stator Blade ◽  
Twisted Blade ◽  
Flow Compressor ◽  
Highly Loaded

In an axial flow compressor, the presence of separated flow near the hub-end of a stator would result in an overall loss in the performance. In the present paper, stator hub-stall is attempted to be eliminated for a high hub-tip ratio (0.8) axial flow compressor stage consisting of a highly loaded rotor and stator. Numerical and experimental studies on an untreated straight stator (straight-stacked, twisted) blade show a large vortex near its hub. The large vortex is attempted to be reduced by modifying the present blade by (i) providing an additional twist at the hub-end of the stator blade (ii) providing a hub-clearance (a cantilevered blade fixed from the casing). The straight (untreated) stator, hub-end-bend version and the hub-clearance version are studied for two different rotor-tip clearances. Detailed computational analysis of the variation of hub-clearance at a fixed rotor-tip clearance is also carried out. Throughout the study, experiments are carried out on the above discussed different stator (untreated & hub-treated) configurations, in combination with the same rotor, at a fixed rotor-tip clearance. The studies show that the flow conditions are improved near the hub of the highly loaded stator blade both by the hub-end-bend design and by the hub-clearance provided.

Effect of hub clearance of cantilever stator on aerodynamic performance and flow field of a transonic axial-flow compressor

2021 ◽  
pp. 095441002199370
Author(s):  
Botao Zhang ◽  
Bo Liu ◽  
Xiaochen Mao ◽  
Hejian Wang
Keyword(s):  
Flow Field ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Aerodynamic Performance ◽  
Tip Clearance ◽  
Leakage Flow ◽  
Stall Margin ◽  
Axial Flow Compressor ◽  
Stator Blade ◽  
Flow Compressor

To investigate the effect of hub clearance of cantilever stator on the aerodynamic performance and the flow field of the transonic axial-flow compressor, the performance of single-stage compressors with the shrouded stator and cantilever stator was studied numerically. It is found that the hub corner separation on the stator blade suction surface (SS) was modified by introducing the hub leakage flow. The separation vortex on the SS of the stator blade root at about 10% axial chord length caused by the interaction of the shock wave and boundary layer was also controlled. Compared with the tip clearance size of the rotor blade, the stator hub clearance size (HCS) has a much less effect on the overall aerodynamic performance of the compressor, and there is no obvious effect on the flow field in the upstream blade row. With the increase of HCS, the leakage loss and the blockage degree in the flow field near the stator hub are increased and further make the adiabatic efficiency and the total pressure ratio of the compressor gradually decrease. Meanwhile, the stall margin of the compressor was changed slightly, but the response of the stall margin to the change of the HCS is nonlinear and insensitive. The stator hub leakage flow (HLF) can not only change the flow field near the hub but also redistribute the flow law within the range of the entire blade span. It will contribute to further understand the mechanism of the HLF and provide supports for the design of the cantilever stator of transonic compressors.

scholarly journals Experimental Investigation of the Flow Field in a Multistage Axial Flow Compressor

1994 ◽  
Author(s):  
B. Lakshminarayana ◽  
N. Suryavamshl ◽  
J. Prato ◽  
R. Moritz
Keyword(s):  
Flow Field ◽  
Secondary Flow ◽  
Axial Flow ◽  
Suction Side ◽  
Temporal Variations ◽  
Hot Wire ◽  
Suction Surface ◽  
Mean Velocity ◽  
Axial Flow Compressor ◽  
Flow Compressor

The nature of the flow field in a three stage axial flow compressor, including a detailed survey at the exit of an embedded stator as well as the overall performance of the compressor is presented and interpreted in this paper. The measurements include area traverse of a miniature five hole probe (1.07 mm dia) downstream of stator 2, radial traverses of a miniature five hole probe at the inlet, downstream of stator 3 and at the exit of the compressor at various circumferential locations, area traverse of a low response thermocouple probe downstream of stator 2, radial traverses of a single sensor hot-wire probe at the inlet, and casing static pressure measurements at various circumferential and axial locations across the compressor at the peak efficiency operating point. Spectral analysis of the hot-wire data reveal the existence of several harmonics of all three rotor blade passing frequencies at the inlet of the compressor. Mean velocity, pressure and total temperature contours as well as secondary flow contours at the exit of the stator 2 are reported and interpreted. Hub clearance flow is shown to eliminate the suction surface corner separation. Secondary flow contours show the migration of fluid particles toward the core of the low pressure regions located near the suction side casing endwall corner. The RMS value of the spatial fluctuations in mean velocity downstream of the second stator (which appear as temporal variations to the subsequent rotor) have been derived and shown to be significant.

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