A numerical study of shock wave/boundary layer interaction in a supersonic compressor cascade

Song, Dong Joo; Hwang, Hyun Chul; Kim, Young In

doi:10.1007/bf03185220

Cited by 3 publications

(3 citation statements)

References 15 publications

(10 reference statements)

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“…In [4], an in-depth parametric study was carried out in order to investigate the influence of the leading-edge radius, cascade solidity, and pre-compression on the aerodynamic performance of a supersonic cascade. In [5], another numerical analysis of SWBLI in transonic/supersonic axial flow compressor cascade was performed, showing the results of various turbulence models. A one-dimensional analytical shock loss model was proposed in [6] for optimizing the shock structure in a supersonic cascade.…”

Section: Introductionmentioning

confidence: 99%

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

2019

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Modern aeronautic fans are characterised by a transonic flow regime near the blade tip. Transonic cascades enable higher pressure ratios by a complex system of shockwaves arising across the blade passage, which has to be correctly reproduced in order to predict the performance and the operative range. In this paper, we present an accurate two-dimensional numerical modelling of the ARL-SL19 transonic compressor cascade. A large series of data from experimental tests in supersonic wind tunnel facilities has been used to validate a computational fluid dynamic model, in which the choice of turbulence closure resulted critical for an accurate reproduction of shockwave-boundary layer interaction. The model has been subsequently employed to carry out a parametric study in order to assess the influence of main flow variables (inlet Mach number, static pressure ratio) and geometric parameters (solidity) on the shockwave pattern and exit status. The main objectives of the present work are to perform a parametric study for investigating the effects of the abovementioned variables on the cascade performance, in terms of total-pressure loss coefficient, and on the shockwave pattern and to provide a quite large series of data useful for a preliminary design of a transonic compressor rotor section. After deriving the relation between inlet and exit quantities, peculiar to transonic compressors, exit Mach number, mean exit flow angle and total-pressure loss coefficient have been examined for a variety of boundary conditions and parametrically linked to inlet variables. Flow visualisation has been used to describe the shock-wave pattern as a function of the static pressure ratio. Finally, the influence of cascade solidity has been examined, showing a potential reduction of total-pressure loss coefficient by employing a higher solidity, due to a significant modification of shockwave system across the cascade.

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Section: Introductionmentioning

confidence: 99%

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

2019

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“…If the numerical calculation diverges, the previous convergent point is taken as the compressor near stall point. (2) When the numerical calculation converges, it is necessary to observe the trajectory of the compressor blade tip clearance leakage flow. If the clearance leakage flow overflows from the leading edge of the blade, the previous convergent point is taken as the compressor near stall point.…”

Section: Methodsmentioning

confidence: 99%

“…Hence, the compressor has always been a focal point for researchers. With the ongoing pursuit of a high thrust-to-weight ratio, fuel efficiency, and meeting the power demands of aircraft with higher cruising speed, the high-pressure compressor has emerged as a vital research area in advanced compressor technology [1,2].…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Aerodynamic Performance and Flow Mechanism of Transonic Ultra-Highly Loaded Tandem-Rotor Stage

Yuan,

Wu,

Zhao

et al. 2024

Aerospace

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The compressor serves as a crucial component that influences the performance of the gas turbine engine. Researchers have been endeavoring to explore compressor types that possess a high loading level and high-efficiency characteristics concurrently. In this study, tandem blade technology was applied to a transonic ultra-highly loaded axial compressor, and the Baseline single-blade rotor was replaced by a tandem rotor to take into account the loading level and compressor performance. Detailed investigations were carried out to identify the effects on the aerodynamic performance of the ultra-highly loaded stage and the fundamental flow mechanism within the tandem-rotor stage. This paper presents original design maps for the tandem-rotor stage, and the selection criteria for tandem parameters in tandem-rotor stage are refined. The results indicate that the peak efficiency improved by 0.83%, the stall margin increased by 2.16%, and the choke flow rate rose by 0.30% for the optimal tandem-rotor configuration. The meridional division position of the rotor primarily affects the ratio of loading of the front and rear blades, while the circumferential relative position of the tandem rotor mainly influences the channel types formed by the front and rear blades. Larger values for the meridional division position parameter and smaller values for circumferential relative position parameter should be selected for the tandem rotor design to optimize both the isentropic efficiency and total pressure ratio. This investigation offers the theoretical foundation for the design of a transonic ultra-highly loaded tandem-rotor compressor.

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Comparison of turbulence models in shock-wave/boundary-layer interaction

Kim

Kwon

Song

2004

KSME International Journal

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This paper presents a comparative study of a fully coupled, upwind, compressible NavierStokes code with three two-equation models and the Baldwin-Lomax algebraic model in predicting transonic/supersonic flow. The k-e turbulence model of Abe performed well in predicting the pressure distributions and the velocity profiles near the flow separation over the axisymmetric bump, even though there were some discrepancies with the experimental data in the shear-stress distributions. Additionally, it is noted that this model has y* in damping functions instead of y÷. The turbulence model of Abe and Wilcox showed better agreements in skin friction coefficient distribution with the experimental data than the other models did for a supersonic compression ramp problem. Wilcox's model seems to be more reliable than the other models in terms of numerical stability. The two-equation models revealed that the redevelopment of the boundary layer was somewhat slow downstream of the reattachment portion.

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A numerical study of shock wave/boundary layer interaction in a supersonic compressor cascade

Cited by 3 publications

References 15 publications

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

Investigation on the Aerodynamic Performance and Flow Mechanism of Transonic Ultra-Highly Loaded Tandem-Rotor Stage

Comparison of turbulence models in shock-wave/boundary-layer interaction

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