scholarly journals Discussion: “Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 2—Unsteady Flow and Pressure Field” (Schulz, H. D., Gallus, H. E., and Lakshminarayana, B., 1990, ASME J. Turbomach., 112, pp. 679–688)

1990 ◽  
Vol 112 (4) ◽  
pp. 689-689
Author(s):  
R. L. Evans
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Pressure Field ◽  
Three Dimensional ◽  
Separated Flow ◽  
Compressor Cascade ◽  
Rotor Stator Interaction

Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part I — Quasi-Steady Flow Field and Comparison With Steady-State Data

1989 ◽  
Author(s):  
H. D. Schulz ◽  
H. E. Gallus ◽  
B. Lakshminarayana
Keyword(s):  
Flow Field ◽  
Separation Bubble ◽  
Three Dimensional ◽  
Separated Flow ◽  
Major Influence ◽  
Compressor Cascade ◽  
Three Dimensional Flow ◽  
Dimensional Flow ◽  
Corner Flow ◽  
Rotor Stator Interaction

An experimental study of three-dimensional flow field in an annular compressor cascade with an upstream rotor has been carried out at four different incidences to the stator blade. Blade boundary layers and the three-dimensional flow field at the exit are surveyed using a hot wire sensor and a five hole probe, respectively. The data on the blade boundary layer, passage flow and separated corner flow is presented. The upstream rotor wake has a major influence on the transition, laminar separation bubble, extent of wall/corner flow separation, aerodynamic losses, secondary flow and three-dimensional flow inside the passage. Detailed interpretation of the effects of upstream wakes on the entire passage flow is presented and compared with the data in the absence of a rotor.

Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 1—Quasi-Steady Flow Field and Comparison With Steady-State Data

1990 ◽  
Vol 112 (4) ◽  
pp. 669-678 ◽  
Author(s):  
H. D. Schulz ◽  
H. E. Gallus ◽  
B. Lakshminarayana
Keyword(s):  
Flow Field ◽  
Separation Bubble ◽  
Three Dimensional ◽  
Separated Flow ◽  
Major Influence ◽  
Compressor Cascade ◽  
Three Dimensional Flow ◽  
Dimensional Flow ◽  
Corner Flow ◽  
Rotor Stator Interaction

An experimental study of three-dimensional flow field in an annular compressor cascade with an upstream rotor has been carried out at four different incidences to the stator blade. Blade boundary layers and the three-dimensional flow field at the exit are surveyed using a hot-wire sensor and a five-hole probe, respectively. The data on the blade boundary layer, passage flow, and separated corner flow are presented. The upstream rotor wake has a major influence on the transition, laminar separation bubble, extent of wall/corner flow separation, aerodynamic losses, secondary flow, and three-dimensional flow inside the passage. A detailed interpretation of the effects of upstream wakes on the entire passage flow is presented and compared with the data in the absence of a rotor.

Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part II — Unsteady Flow and Pressure Field

1989 ◽  
Author(s):  
H. D. Schulz ◽  
H. E. Gallus ◽  
B. Lakshminarayana
Keyword(s):  
Boundary Layers ◽  
Pressure Field ◽  
Pressure Fluctuations ◽  
Three Dimensional ◽  
Separated Flow ◽  
Leading Edge ◽  
Fast Response ◽  
Compressor Cascade ◽  
Rotor Stator Interaction ◽  
Detailed Interpretation

An experimental study of the unsteady three-dimensional flow and pressure field in an annular compressor cascade with an upstream rotor has been carried out at several incidences to the stator blade. The distribution of the unsteady pressures at the blade surfaces are measured using fast response Kulite sensors. The unsteady blade boundary layers and the passage flow is measured with a hot wire sensor. Detailed interpretation of the magnitude of unsteady pressures, phase angle differences, unsteady blade boundary layers, wake transport through the stator passage is presented and analyzed in the paper. The unsteady pressures are found to be dominant near the blade leading edge. Substantially higher pressure fluctuations occur in this region as well as on the edge of the corner flow separation region.

Three-Dimensional Separated Flow Field in the Endwall Region of an Annular Compressor Cascade in the Presence of Rotor-Stator Interaction: Part 2—Unsteady Flow and Pressure Field

1990 ◽  
Vol 112 (4) ◽  
pp. 679-688 ◽  
Author(s):  
H. D. Schulz ◽  
H. E. Gallus ◽  
B. Lakshminarayana
Keyword(s):  
Boundary Layers ◽  
Pressure Field ◽  
Pressure Fluctuations ◽  
Three Dimensional ◽  
Separated Flow ◽  
Leading Edge ◽  
Fast Response ◽  
Compressor Cascade ◽  
Rotor Stator Interaction ◽  
Detailed Interpretation

An experimental study of the unsteady three-dimensional flow and pressure field in an annular compressor cascade with an upstream rotor has been carried out at several incidences to the stator blade. The distributions of the unsteady pressures at the blade surfaces are measured using fast response Kulite sensors. The unsteady blade boundary layers and the passage flow are measured with a hot-wire sensor. A detailed interpretation of the magnitude of unsteady pressures, phase angle differences, unsteady blade boundary layers, and wake transport through the stator passage is presented and analyzed in the paper. The unsteady pressures are found to be dominant near the blade leading edge. Substantially higher pressure fluctuations occur in this region as well as on the edge of the corner flow separation region.

scholarly journals Analysis of Separated Flows Inside an Annular Compressor Cascade Using a Low-Re-Number k-ϵ and an Algebraic Reynolds-Stress-Model

1997 ◽  
Author(s):  
Jürgen R. Lücke ◽  
Heinz E. Gallus
Keyword(s):  
Flow Field ◽  
Reynolds Stress ◽  
Three Dimensional ◽  
Separated Flow ◽  
Reynolds Stress Model ◽  
Stress Model ◽  
Mean Flow ◽  
Compressor Cascade ◽  
Production Term ◽  
Algebraic Reynolds Stress Model

The flow field inside an annular compressor cascade is numerically investigated. The mean flow features are complex three-dimensional zones of turbulent separation at hub and shroud at high inflow angles. The flow field is investigated with an implicit three-dimensional Navier-Stokes code. To predict turbulent effects the flow solver includes two different variants of a Low-Re-number k-ϵ-model and an algebraic Reynolds-stress-model. Using the Low-Re-number model the structure of the regions of separated flow are fairly well predicted. However, intensity and size of these zones are too small compared with the experimental data. Better results are produced using the anisotropic algebraic Reynolds-stress-model combined with a stagnation point modification of the turbulent production term. Stucture and intensity of the vortex systems are simulated in more detail. Static pressure distributions and loss contours are in a very good agreement with the experiments.

Three-Dimensional Wake Decay Inside of a Compressor Cascade and Its Influence on the Downstream Unsteady Flow Field: Part II—Unsteady Flow Field Downstream of the Stator

1991 ◽  
Vol 113 (2) ◽  
pp. 190-197 ◽  
Author(s):  
C. Poensgen ◽  
H. E. Gallus
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Turbulent Flows ◽  
Velocity Vector ◽  
Three Dimensional ◽  
Time Dependent ◽  
Major Influence ◽  
Hot Wire ◽  
Compressor Cascade ◽  
Turbulent Flow Field

A measuring technique based on multisensor hot-wire anemometry has been developed to determine the unsteady three-dimensional velocity vector and the structure of turbulent flows. It then has been applied to the passage and the exit flow of an annular compressor cascade, which is periodically disturbed by the wakes of a cylinder rotor, located about 50 percent of blade chord upstream. In Part I of this paper the decay of the rotor wakes has been described first without stator and secondly through a stator passage. The time-dependent turbulent flow field downstream of this stator is discussed in Part II of this paper. The rotor wakes have a major influence on the development of three-dimensional separated regions inside the compressor cascade, and this interaction will be addressed in both parts of the paper.

Three-Dimensional Wake Decay Inside of a Compressor Cascade and its Influence on the Downstream Unsteady Flow Field: Part II — Unsteady Flow Field Downstream of the Stator

1990 ◽  
Author(s):  
C. Poensgen ◽  
H. E. Gallus
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Turbulent Flows ◽  
Velocity Vector ◽  
Three Dimensional ◽  
Time Dependent ◽  
Major Influence ◽  
Hot Wire ◽  
Compressor Cascade ◽  
Turbulent Flow Field

A measuring technique based on multi-sensor hot-wire anemometry has been developed to determine the unsteady three-dimensional velocity vector and the structure of turbulent flows. It then has been applied to the passage and the exit flow of an annular compressor cascade, which is periodically disturbed by the wakes of a cylinder rotor, located about 50 percent of blade chord upstream. In Part I of this paper the decay of the rotor wakes will be described first without stator and secondly through a stator passage. The time-dependent turbulent flow field downstream of this stator is discussed in Part II of this paper. The rotor wakes have a major influence on the development of three-dimensional separated regions inside the compressor cascade, and this interaction will be addressed in both parts of this paper.

Three-Dimensional Unsteady Flow Field due to Rotor-Stator Interaction in the Tip Region of an Axial Compressor Stator Passage

2001 ◽  
Author(s):  
Hongwei Ma ◽  
Haokang Jiang ◽  
Qingguo Zhang
Keyword(s):  
Flow Field ◽  
Unsteady Flow ◽  
Measurement Techniques ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Low Energy ◽  
Separation Flow ◽  
Rotor Wake ◽  
Flow Mixing ◽  
Rotor Stator Interaction

This paper reports an experimental study of the three-dimensional unsteady flow field due to rotor-stator interaction in the tip region of an axial compressor stator passage. The measurements were conducted on a low-speed large-scale axial compressor using a 3-component Laser Doppler Velocimetry. Both experimental method and measurement techniques are presented in details. The measurement results indicate that the rotor tip leakage vortex and the rotor wake periodically pass through the tip region of a stator passage, resulting in periodical flow blockages and fluctuations in the stator passage. In the meantime, the wake is catching up with the last rotor leakage vortex. The interaction and the flow mixing between the vortex and the wake occur in a stator passage, leading to more substantial fluctuations in the flow field. The rotor lip leakage vortex has a stronger influence on the downstream endwall flow than the rotor wake. The low-energy fluids from the upstream tend to accumulate toward the pressure surface of a stator blade. The separation flow near the suction surface is found in the rear of a stator passage. The interaction and the flow mixing are observed among the low-energy fluids from the upstream and the separation flow.

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