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

Schulz, Henrik; Gallus, H. E.; Lakshminarayana, B.

doi:10.1115/89-gt-76

Cited by 9 publications

(18 citation statements)

References 7 publications

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“…12). This three-dimensional flow structure for corner separation was first derived by Schulz et al [5] and has been proved by other researchers by numerical simulations [3,7,13,26]. The appearance of the limiting streamlines for the type B flow can be seen in Fig.…”

Section: Topological Analyses Of Typical 3d Flow Structuresmentioning

confidence: 72%

“…The accumulation of significant low momentum flows at the upstream rotor tip after the maximum static pressure rise condition causes a locally increase of the incidence angle at the stator blade tip and results in the leading edge suction side near casing corner separation. (5) The measured results at the near-stall condition obtained by SPIV were used for validating the topological analyses based on the oil-flow visualization results in the paper. The results show that the topological analyses and the reconstructed 3D flow structures in the tested stator passage are reliable.…”

Section: Discussionmentioning

confidence: 99%

“…Only one of the two separation lines ends with a spiral node, another one flows downstream directly. In the experiments conducted by Schulz et al [5], they did not observe this type of flow. However, according to the numerical simulation results given by Hah and Loellbach [7] and Weber et al [26], the corner separation of flow type C may occur when the back pressure decreases below a certain value.…”

Section: Topological Analyses Of Typical 3d Flow Structuresmentioning

confidence: 93%

“…It is well known that the topological analysis of the limiting streamlines is helpful for the reconstruction of the 3D flow structures [17][18][19][20] and has been widely used for studying complex flows in turbomachinery [5,10,23,24]. In the above section we have discussed the evolutionary process of 3D separation flows in the tested stator passage.…”

Section: Topological Analyses Of Typical 3d Flow Structuresmentioning

confidence: 97%

“…Hence, in the past few decades, it was always a key flow phenomenon concerned by compressor aerodynamicists. Great amount of researches were conducted for clarifying the flow mechanisms and aerodynamic features in turbomachinery by experimental, theoretical, and numerical methods [4][5][6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Zhang

Liu

2013

Experimental Thermal and Fluid Science

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Section: Topological Analyses Of Typical 3d Flow Structuresmentioning

confidence: 72%

Section: Discussionmentioning

confidence: 99%

Section: Topological Analyses Of Typical 3d Flow Structuresmentioning

confidence: 93%

Section: Topological Analyses Of Typical 3d Flow Structuresmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Zhang

Liu

2013

Experimental Thermal and Fluid Science

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Experimental investigation of the effect of rotor tip gaps on 3D separating flows inside the stator of a highly loaded compressor stage

Liu

et al. 2016

Experimental Thermal and Fluid Science

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Flow separations in compressor blade passages are common and can cause significant flow blockage and loss production. This paper investigates experimentally the three-dimensional (3D) flow separations in a highly loaded low-speed large-scale compressor facility. Oil flow visualizations, stereoscopic particle image velocimetry (SPIV), and five-hole probe measurements are conducted at certain conditions from the near-chock to near-stall condition along the compressor operating line. The 3D separation and vortex flow structures in the stator at different operating conditions are analyzed. By changing the size of the rotor tip gap, six groups of oil-flow pictures are obtained to study the effect of the rotor gaps on the 3D separating flows in the downstream stator. The variation of the corner separation scale is almost linear with the rotor tip gap size. Along the compressor operating line, four typical 3D flow structures are found inside the stator passage. Between the second typical 3D flow structure and the third typical 3D flow structure, an unstable stage exists on the compressor operating line; during this stage, the hub corner separation becomes an open separation from the closed type. A smaller rotor tip gap corresponds to an earlier unstable stage. Finally, a critical rotor tip blockage state usually existed for the transform of corner separation types at a certain rotor tip gap configuration. This discovery is valuable for the study of multistage compressor matching problems at off-design conditions.

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3-D Transonic Flow in a Compressor Cascade With Shock-Induced Corner Stall

Weber

Schreiber

Fuchs

et al. 2002

Journal of Turbomachinery

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An experimental and numerical study of the transonic flow through a linear compressor cascade with endwalls was conducted. The cascade with a low aspect ratio of 1.34 was tested at an inlet Mach number of 1.09 and a Reynolds number of 1.9×106. Detailed flow visualizations on the surfaces and five-hole probe measurements inside the blading and in the wake region showed clearly a three-dimensional boundary layer separation on the blade surface and the sidewall, and a severe corner stall induced by a strong 3-D shock system at blade passage entrance. The experimental data have been used to validate and improve the 3-D Navier-Stokes code TRACE. Results showed an excellent resolution of the complex flow field. Surface pressure distributions on the entire blade surface and the endwalls, flow angle and total pressure contours within the blade passage and the wake are compared with the experimental results. An analysis of the secondary flow of this highly staggered cascade did not show the classical corner vortex. Instead, a severe flow deviation and partly reverse flow near the walls is seen. The flow solver helped to identify a weak ring vortex that originates from the passage sidewall. Surface oil flow pictures on the blade contour and the sidewall are in qualitatively good agreement to numerical surface streaklines. A considerable improvement of the numerical results could be achieved by a gradual grid refinement, especially in the corner region and by successive code development.

show abstract

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

Cited by 9 publications

References 7 publications

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Experimental investigation of the effect of rotor tip gaps on 3D separating flows inside the stator of a highly loaded compressor stage

3-D Transonic Flow in a Compressor Cascade With Shock-Induced Corner Stall

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