Numerical identification of separation bubble in an ultra-high-lift turbine cascade using URANS simulation and proper orthogonal decomposition

Sajadmanesh, Seyed Morteza; Mojaddam, Mohammad; Mohseni, Arman; Nikparto, Ali

doi:10.1016/j.ast.2019.105329

Cited by 24 publications

(8 citation statements)

References 26 publications

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“…Proper Orthogonal Decomposition (POD) has been used to capture the orthogonal eigenvectors representing intrinsic systematic information, 48 which is ordered by variance with directions perpendicular to each other. [49][50][51][52] POD is applied in this paper to form new design variables as combinations of group of control point displacement, representing the trend of blade shape deformation. In the implementation of POD, let z (i) be line of 48 control point displacement representing a certain blade surface shape deformation.…”

Section: Proper Orthogonal Decompositionmentioning

confidence: 99%

See 1 more Smart Citation

An approach of Proper Orthogonal Decomposition-aided Free-form Deformation with application in compressor blade design

Wang

Qin

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Compressor blade design influences aero-engine performance mainly through its total pressure ratio and efficiency. As a volume-based geometric parameterization, Free-form Deformation (FFD) brings three-dimensionality that is essential to blade design. However, the manipulation of control points with respect to simple numeric parametric perturbation renders the use of design space low-efficient. Therefore, an improved FFD with ‘wiser’ control point lay-out is expected to identify those more important design variables. This paper proposes novel design variables that are assigned to grouping of control points’ displacement in FFD lay-out. In short, the approach is realized as: (i) establish a library of sufficient blade shape samples; (ii) filter the database with geometric constraints; (iii) extract dominant modes via (POD) Proper Orthogonal Decomposition; (iv) construct new design variables and apply them in optimization. With geometric constraint filtering, problem-oriented information is injected. With POD, the dominance of new selected geometric parameters in problem description is assured. Perfunctory details of displacement data of each control point in the lay-out can be replaced by grouped data as new design variable candidates. As a proof-of-concept study of the new approach, compressor blade Rotor 37 is selected to be the good platform of testing the feasibility of POD-aided FFD as a global and flexible yet economic geometric parameterization. Result demonstrates the feasibility of proposed POD-aided FFD approach that helps conduct an optimization involving displacement of 6 × 4 × 3 control points with as few as five new design variables, while still being capable of bringing optimization effect in three test cases.

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Section: Proper Orthogonal Decompositionmentioning

confidence: 99%

Section: Proper Orthogonal Decompositionmentioning

confidence: 99%

An approach of Proper Orthogonal Decomposition-aided Free-form Deformation with application in compressor blade design

Wang

Qin

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…The flow decomposition technique is used to distinguish different flow patterns that occur within a compressor. POD and DMD methods are commonly applied to pressure fields to study the internal flow of fluid machinery in the literature [25][26][27][28][29]. The modal decomposition methods are suitable for the study of pressure loss and flow instability caused by stall cell and impeller-diffuser interaction near the shroud side of the diffuser.…”

Section: Flow Field Modal Decompositionmentioning

confidence: 99%

Numerical Study of the Improvement in Stability and Performance by Use of a Partial Vaned Diffuser for a Centrifugal Compressor Stage

Liu

et al. 2021

Applied Sciences

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The influence of different diffuser configurations on the flow stability and aerodynamic performance of a centrifugal compressor stage with a mass flow coefficient of 0.196 is numerically investigated. Research results show that the performance of a traditional full-height vaned diffuser (TVD) deteriorates rapidly, and a shroud-side partial vaned diffuser (SVD) displays better adaptability in off-design conditions. SVD can suppress the development of vortices generating at the diffuser leading-edge. Therefore, it can reduce the flow loss inside the stage and improve the flow stability of the stage at low mass flow rates. The unsteady analysis for TVD and SVD shows that the stall cell propagates at about 35.7% of impeller rotational speed in the semi-vaneless space and diffuser passages. Furthermore, the internal flow in TVD and SVD is studied by employing the proper orthogonal decomposition (POD) and dynamic mode decomposition (DMD) methods. The flow loss and instability mechanism in the stage are consequently revealed more comprehensively.

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“…System identification [14] and Proper Orthogonal Decomposition (POD) [15] are the two most commonly used ROMs in CFD-based aeroelastic analysis. The CFD-based ROMs have been also exercised for transonic [16] and hypersonic [17] aeroelastic analysis, limit-cycle oscillation (LCO) [18], gust response analysis [19], aerodynamic shape optimisation [20,21], and blade aerodynamic force [22,23]. In particular, the last decade has witnessed various studies on the developments of the CFD-based ROMs for active flutter suppression.…”

Section: Introductionmentioning

confidence: 99%

An efficient reduced-order framework for active/passive hybrid flutter suppression

Wang

Ronch

et al. 2022

Aeronaut. j.

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Flutter suppression is an important measure to improve fatigue life and enhance the performance of aircraft in modern aircraft design. In order to design more effective controllers for flutter suppression with high efficiency, an efficient reduced-order framework for active/passive hybrid flutter suppression is proposed. The traditional CFD-based ROMs have been successfully applied to active flutter suppression with high accuracy and efficiency. But, when a structure modification is made such as in aeroelastic tailoring and aeroelastic structural optimisation, the structural model should be updated, and the expensive, time-consuming CFD-based ROMs have to be reconstructed; such a process is impractical for passive flutter suppression. To overcome the realistic challenge, an efficient reduced-order framework for active/passive hybrid flutter suppression is proposed by extending an efficient aeroelastic CFD-based POD/ROM which we have developed. The proposed framework is demonstrated and evaluated using an improved AGARD 445.6 wing model. The results show that the proposed framework can accurately predict the aeroelastic response for active/passive hybrid flutter suppression with high efficiency. It provides a powerful tool for active/passive hybrid flutter suppression, and therefore, is ideally suited to design more effective controllers, and may have the potential to reduce the overall cost of aircraft design.

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Numerical identification of separation bubble in an ultra-high-lift turbine cascade using URANS simulation and proper orthogonal decomposition

Cited by 24 publications

References 26 publications

An approach of Proper Orthogonal Decomposition-aided Free-form Deformation with application in compressor blade design

An approach of Proper Orthogonal Decomposition-aided Free-form Deformation with application in compressor blade design

Numerical Study of the Improvement in Stability and Performance by Use of a Partial Vaned Diffuser for a Centrifugal Compressor Stage

An efficient reduced-order framework for active/passive hybrid flutter suppression

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