Compressor cascade flow with strong shock-wave/boundary-layer interaction

Küsters, Bernhard; Schreiber, H. A.

doi:10.2514/3.14087

Cited by 8 publications

(7 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The increasing of viscous loss due to the strong boundary layer separation on the suction side can be mitigated only by increasing the AVDR, as was experimentally demonstrated in [12], because SWBLI effect and wake thickness are reduced, increasing flow turning and improving ω. This loss reduction due to a larger AVDR is more pronounced at higher static pressure ratios, as demonstrated in [12] for the present cascade and in [3] for a similar one. Since all the simulations were carried out with a unity AVDR, the overall behavior of the total-pressure loss coefficient was affected only by the static pressure ratio and not by the AVDR.…”

Section: Total-pressure Loss Coefficientsupporting

confidence: 75%

“…On the other hand, numerical simulations can support the experimental analysis of transonic flows in compressors, focusing on some aspects which cannot be easily investigated in an experimental arrangement. Once the numerical model has been properly validated by using available experimental data, it can provide excellent results when employed for further analysis (e.g., [3,4]).…”

Section: Introductionmentioning

confidence: 99%

“…Various studies were carried out in order to investigate a large number of topics related to transonic compressor rotors and cascades. For example, in [3] numerical simulations were performed in order to study the shock-wave/boundary-layer interaction (SWBLI) in a transonic compressor cascade. A two-dimensional Navier-Stokes solver was validated using experimental data obtained in a supersonic cascade facility in order to investigate the influence of inlet Mach number and axial velocity-density ratio (AVDR) on blade performance.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

2019

View full text Add to dashboard Cite

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.

show abstract

Section: Total-pressure Loss Coefficientsupporting

confidence: 75%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

2019

View full text Add to dashboard Cite

show abstract

“…With this improvement, the modified cascade achieves about 16% reduction of the total pressure loss in the simulated operation range and the majority of this loss reduction comes from the decrease of the passage shock losses (see Figure 21(a)). Moreover, the entropy contour in Figure 21(b) shows that the high shock loss region, generated by the quasi-normal shock and lambda shock, 37,40 disappears in the modified cascade and the loss level of this region has been significantly reduced, which demonstrates the analysis results from the developed model. The above aerodynamic modification suggested by the analytical model for DLR-PAV-1.5 shows rather consistency with the numerical optimization results obtained by Venturelli and Benini.…”

Section: Optimized Resultsmentioning

confidence: 70%

“…To validate the effectiveness of the developed model, it is applied to optimize the shock structures of two supersonic cascades ARL-SL19 and PAV-1.5 for which detailed experimental data are available, 9,12,19,22,37 with the objective of reducing the total pressure loss while maintaining the aerodynamic load. The geometry of the two cascades is shown in Figure 9 with parameters given in Table 4.…”

Section: Application Of Analytical Shock Loss Model For Shock System mentioning

confidence: 99%

A new method for rapid shock loss evaluation and reduction for the optimization design of a supersonic compressor cascade

Liu

Shi

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

A one-dimensional analytical shock loss prediction method was proposed to tailor the shock system, i.e. the strength of the first and second passage shock, and reduce the shock loss in a supersonic cascade. To develop the one-dimensional analytical model, the shock system in a supersonic cascade was divided into four processes which can be seen in most supersonic compressor cascade, i.e. the flow upstream the extending-external shock, the flow between the extendingexternal shock and the first passage shock, the accelerating flow from the first passage shock to the second passage shock, and the flow downstream of the second passage shock. Based on some flow assumptions and experimental empirical correlations, the complex flows, containing the shock system, in the blade passage of a supersonic compressor cascade could be described with one-dimensional relationships, which can be used to predict shock losses along the flow passage rapidly and determine the shock system improving direction for achieving lower shock loss while keeping the same cascade static pressure ratio. In order to validate the one-dimensional analytical method, the shock system of two supersonic cascades ARL-SL19 and DLR-PAV-1.5 are modified based on the analysis of the model. The modified cascades achieved about 29% and 25% reduction of shock loss at redesign point compared with baseline cascades, respectively.

show abstract

A comprehensive analysis of flow blowing and its effects on change in main flow conditions and loss generation in compressible flows

Sarimurat

2022

Aerospace Science and Technology

View full text Add to dashboard Cite

Compressor cascade flow with strong shock-wave/boundary-layer interaction

Cited by 8 publications

References 0 publications

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

Accurate 2-D Modelling of Transonic Compressor Cascade Aerodynamics

A new method for rapid shock loss evaluation and reduction for the optimization design of a supersonic compressor cascade

A comprehensive analysis of flow blowing and its effects on change in main flow conditions and loss generation in compressible flows

Contact Info

Product

Resources

About