Analysis of Three-Dimensional Viscous Flow in a Supersonic Axial Flow Compressor Rotor With Emphasis on Tip Leakage Flow

Perrin, G.; Leboeuf, Francis; Dawes, W. N.

doi:10.1115/92-gt-388

Cited by 8 publications

(4 citation statements)

References 12 publications

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“…A semi-empirical formula for the tip vortex trajectory inside the blade passage, developed by Chen et al (1991), shows the vortex path to be independent of the gap width and to be governed primarily by inviscid convective phenomena. Simulations by Perrin et al (1992) indicate a rapid decay of vorticity in the vortex core over 30% of the rotor chord in a transonic compressor. A large influence of the clearance width on shock structure and efficiency of a transonic compressor rotor is reported by several authors, see e.g.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Shock-Tip Leakage Vortex Interaction in a HPC Front Stage

Hoeger

Fritsch

Bauer

1998

Volume 1: Turbomachinery

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For a single-stage transonic compressor rig at the TU Darmstadt 3D viscous simulations are compared to L2F-measurements and data from the EGV leading edge instrumentation to demonstrate the predictive capability of the Navier-Stokes code TRACE_S. In a second step the separated regions at the blade tip are investigated in detail to gain insight into the mechanisms of tip leakage vortex-shock interaction at operating points close to stall, peak efficiency and choke. At the casing the simulations reveal a region with axially reversed flow, leading to a rotationally asymmetric displacement of the outermost stream surface and a localized additional pitch-average blockage of app. 2%. Loss mechanisms and streamline patterns deduced from the simulation are also discussed. Although the flow is essentially 3D, a simple model for local blockage from tip leakage is demonstrated to significantly improve 2D-simulations on S1-surfaces.

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Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Shock-Tip Leakage Vortex Interaction in a HPC Front Stage

Hoeger

Fritsch

Bauer

1998

Volume 1: Turbomachinery

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“…Despite a very crude representation of the tip gap region (applying periodicity along six cells spanning the gap), they obtained surprisingly good agreement between measurements and calculations-thus inferring that tip leakage losses are dominated by inviscid flow phenomena, which can to a first approximation be captured by consideration of massflow and momentum through a suitable control volume, as originally proposed by Denton and Cumpsty(1987). The same code was applied by Perrin et al(1992) on a supersonic axial flow compressor using 150k cells-with 10 cells spanning the gap.…”

Section: Introductionmentioning

confidence: 93%

Investigation of Tip Leakage Effects in Transonic Flow Using a Parallel Unstructured Navier-Stokes Code

Hustad

Bölcs

Wehner³

1997

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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Calculated results for tip flow around two different blade configurations are presented and compared with experimental data. The first configuration (case number 1) is a flat-plate profile tested in a linear transonic tunnel — the profile is an idealized representation of the aft-section of some highly curved turbine blades. The second configuration (case number 2) originates from the outer profile on the last-stage-blade of a steam turbine, however it is also reminiscient of a section from a turbine blade with supersonic exit flow. This configuration was tested in an annular cascade at Mach numbers representative of engine operating conditions. The computed results were obtained using a parallel 3D unstructured Navier-Stokes code. The code runs on a work-station cluster, as well as being optimized for the 256 processor Cray T3D at EPFL: the code is capable of gigaflop performance using more than 3 million cells — adaptive mesh refinement thus allows enhanced resolution within the tip gap region. For each configuration we have calculated two Runs. In both cases, Run-1 is similar to the experimental conditions, so that direct comparison between measured and calculated results is possible. With case number 1/Run-2 we re-calculated the flow without imposing a prescribed inflow boundary-layer along the sidewall. Comparison between the two runs helped reveal how free-stream total pressure can establish itself within the tip gap region. For the second configuration — in the annular cascade — we were interested in observing the influence of relative movement between the blade tip and adjacent sidewall. Hence for case number 2/Run-2 we imposed a circumferential velocity on the adjacent sidewall. This modified the effective sidewall boundary-layer and had a noticeable influence on the development of the tip-leakage flow.

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“…Tip leakage flow (Perrin and Leboeuf 1992;Shi and Fu 2013;Qiao et al 2019) and its interaction with passage shock wave (Chunill and Rabe Douglas 2004) are the main flow structures near the casing of transonic compressor rotors, which are related to loss production and stall inception (Sun et al 2020). Yamada et al (2004) revealed the flow phenomena of tip leakage vortex in a transonic compressor rotor.…”

Section: Introductionmentioning

confidence: 99%

Influence of Blade Lean on Performance and Shock Wave/Tip Leakage Flow Interaction in a Transonic Compressor Rotor

Cao

Zhang

Liang

et al. 2022

JAFM

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Blade lean has been extensively used in axial compressor stators to control flow separations, but its influence mechanism on transonic compressor rotors remains to be revealed. The aim of this study is to numerically explore the influence of blade lean on the performance and shock wave/tip leakage flow interaction in a transonic compressor rotor. The effects of leaned pattern (positively lean and negatively lean), leaned angle and leaned height were studied. Results showed that, compared with baseline configuration, the efficiency and total pressure ratio of the entire constant rotating speed line of positively leaned rotor were both decreased. The absolute value of peak efficiency was reduced by as much as 4.34% at 20° lean angle, whereas the maximum reduction of peak total pressure ratio was 0.1 at 20° lean angle. The tip leakage flow streamlines of baseline transonic rotor can be divided into two parts, i.e., the primary vortex and secondary vortex which arises after the shock. Due to shock/tip leakage vortex interaction, the primary vortex enlarged and low-momentum region showed up after the shock; under near stall (NS) condition, tip leakage vortex breakdown occurred after interacting with shock. As positively leaned angle increased, the shock and the shock/tip leakage vortex interaction point moved upstream. In addition, the phenomenon of tip leakage vortex breakdown was enhanced. For negatively leaned rotors, as negatively leaned angle increased, the peak efficiency and total pressure ratio showed a tendency of first increasing and then decreasing. At 5° leaned angle, the peak efficiency was increased by 0.8% at most, and the maximum increment of total pressure ratio was 0.05 at 5° leaned angle. Besides, the loading of blade tip reduced and the loading moved toward trailing edge, resulting in the downstream movements of primary vortex, shock front and shock/tip leakage vortex interaction location. The results may help to improve the near tip flow field of transonic compressor rotor with leaned blade technology.

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Analysis of Three-Dimensional Viscous Flow in a Supersonic Axial Flow Compressor Rotor With Emphasis on Tip Leakage Flow

Cited by 8 publications

References 12 publications

Numerical Simulation of the Shock-Tip Leakage Vortex Interaction in a HPC Front Stage

Numerical Simulation of the Shock-Tip Leakage Vortex Interaction in a HPC Front Stage

Investigation of Tip Leakage Effects in Transonic Flow Using a Parallel Unstructured Navier-Stokes Code

Influence of Blade Lean on Performance and Shock Wave/Tip Leakage Flow Interaction in a Transonic Compressor Rotor

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