Shock wave boundary layer interaction on suction side of compressor profile in single passage test section

Flaszyński, Paweł; Doerffer, Piotr; Szwaba, Ryszard; Kaczyński, Piotr; Piotrowicz, Michal

doi:10.1007/s11630-015-0816-9

Cited by 19 publications

(7 citation statements)

References 4 publications

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“…e interblade channel height-to-chord ratio was 0.6. More details of the compressor cascade model configuration are included in [21]. e turbulence level in the nozzle measured upstream of the passage by the LDA system was 0.8%.…”

Section: Methodsmentioning

confidence: 99%

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Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Szwaba

Kaczyński

Telega

2021

Shock and Vibration

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An experimental investigation was carried out to study the effect of the boundary layer transition on the flow dynamics in the blade passage of a compressor cascade. A model of a turbine compressor passage was designed and assembled in a transonic wind tunnel for this purpose. Two different flow control methods were used in the experiment to induce the transition upstream of the shock wave, one concerning the microstep application and the other using distributed roughness strips. Two locations of spanwise microsteps for the transition trigger were chosen, one at the leading edge and the other closer to the shock wave position. The distributed roughness in the form of standard sandpaper strips with different heights was applied in three various locations on the blade upstream of the shock. The main objective of investigations is to present the influence of the laminar and turbulent shock wave-boundary layer interaction on the flow dynamics in a compressor fan passage, and the specific objective is to show how the parameters of particular transition control methods affect the flow dynamics in the investigated channel. The major challenge for this research was to minimize the disturbance caused by the microstep or roughness to the laminar boundary layer, while still ensuring a successful transition. Very interesting results were obtained in the flow control application for the boundary layer transition control, demonstrating a positive effect on the flow unsteadiness in changing the nature of the interaction.

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Section: Methodsmentioning

confidence: 99%

“…e appropriate AVDR in the cascade model (Figure 2) is achieved by using a complex suction system. Details of this system can be found in [21]. e AVDR in the single-passage compressor test section used in the experiment was 1.2, as assumed in the design conditions.…”

Section: Methodsmentioning

confidence: 99%

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Szwaba

Kaczyński

Telega

2021

Shock and Vibration

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“…experimental and numerical investigations of the interaction in the framework of the TFAST project "Transition Location Effect on Shock Wave Boundary Layer Interaction", see Flaszynski et al [6] and Piotrowicz et al [7].…”

Section: Introductionmentioning

confidence: 99%

Simulation of transonic flows through a turbine blade cascade with various prescription of outlet boundary conditions

2018

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“…Besides experimental studies, see e.g. Flaszynski et al [8], there are also some attempts to simulate separation-induced transition due to the shock wave/boundary-layer interaction, see e.g. Teramoto [9] and Luxa et al [10].…”

Section: Introductionmentioning

confidence: 99%

Simulation of Transonic Flow Through a Mid-Span Turbine Blade Cascade With the Separation-Induced Transition

Straka¹,

Příhoda²,

Fenderl³

2017

Topical Problems of Fluid Mechanics 2017

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The paper deals with the numerical simulation of the transonic flow through a mid-span turbine blade cascade by means of an in-house code based on the EARSM turbulence model of Hellsten [4] implemented in the commercial code ANSYS Fluent was used for the comparison. Simulations were carried out for the transonic regime close to the nominal regime. The flow separation on the suction side of the blade is caused by the interaction of the reflected shock wave with the boundary layer. The attention was focused on the modelling of the transition in the separated flow especially on the modelling of the length of the transition region. Numerical results were compared with experimental results.

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Shock wave boundary layer interaction on suction side of compressor profile in single passage test section

Cited by 19 publications

References 4 publications

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Transition Effect on the Flow Dynamics in a Compressor Blade Passage

Simulation of transonic flows through a turbine blade cascade with various prescription of outlet boundary conditions

Simulation of Transonic Flow Through a Mid-Span Turbine Blade Cascade With the Separation-Induced Transition

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