Analysis of the Effect of Multirow and Multipassage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration—Part I: Aerodynamic Excitation

Schoenenborn, Harald

doi:10.1115/1.4038868

Cited by 17 publications

(6 citation statements)

References 21 publications

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“…However, the results from Methel et al showed more than 60% variations in spectral magnitudes of the fundamental forcing frequency due to stator wake variability among investigated passages [4]. In a recent study, Schoenenborn [9] suggested that the aerodynamic excitation can change significantly from blade to blade due to the superposition of the Tyler-Sofrin (or scattered or spinning) modes, which refer to the acoustic interaction with blade rows further upstream or downstream and may have a significant impact on blade forcing.…”

Section: Introductionmentioning

confidence: 92%

Accounting for Circumferential Flow Nonuniformity in a Multistage Axial Compressor

Lou

Matthews²,

Kormanik³

et al. 2023

Journal of Turbomachinery

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The flow field in a compressor is circumferentially non-uniform due to geometric imperfections, inlet flow nonuniformities, and blade row interactions. Therefore, the flow field, as represented by measurements from discrete stationary instrumentation, can be skewed and contribute to uncertainties in both calculated one-dimensional performance parameters and aerodynamic forcing functions needed for aeromechanics analyses. Considering this challenge, this paper documents a continued effort to account for compressor circumferential flow nonuniformities based on discrete, under-sampled measurements. First, the total pressure field downstream of the first two stators in a three-stage axial compressor was measured across half of the annulus. The circumferential nonuniformities in the stator exit flow, including vane wake variability, were characterized. In addition, the influence of wake variation on stage performance calculations and aerodynamic forcing functions were investigated. In the present study for the compressor with an approximate pressure ratio of 1.3 at design point, the circumferential nonuniformity in total pressure yields an approximate 2.4-point variation in isentropic efficiency and 54% variation in spectral magnitudes of the fundamental forcing frequency for the embedded stage. Furthermore, the stator exit circumferential flow nonuniformity is accounted for by reconstructing the full-annulus flow using a novel multi-wavelet approximation method. The features associated with wake-wake interactions accounting for passage-to-passage variations are resolved in the reconstructed total pressure profile, yielding representative mean flow properties and aerodynamic forcing functions.

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Section: Introductionmentioning

confidence: 92%

Accounting for Circumferential Flow Nonuniformity in a Multistage Axial Compressor

Lou

Matthews²,

Kormanik³

et al. 2023

Journal of Turbomachinery

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“…(Frey et al, 2015). A study where the proposed method is applied to a 3D configuration of industrial relevance is published in (Schönenborn, 2017).…”

Section: Application Configurationmentioning

confidence: 99%

Flutter Analysis of an Embedded Blade Row with a Harmonic Balance Solver

Kersken¹,

Frey²,

Ashcroft³

et al. 2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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“…It was found that the IGV-R1-interaction modes can pass through the rotor passage with little attenuation, and concluded that cut-on modes have a huge impact on the unsteady pressure amplitude of the rotor blade. Schoenenborn [18] showed that the R1-S1-R2 interaction modes can lead to different blade excitations in the circumferential direction. Terstegen et al [9,19] investigated the effect of rotor-stator interactions on the rotor blade response of a 2.5-stage axial compressor.…”

Section: Introductionmentioning

confidence: 99%

Forced Response Analysis of an Embedded Compressor Rotor Induced by Stator Disturbances and Rotor–Stator Interactions

2023

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Accurate predictions of the blade response in a multi-row compressor is one of the most important tasks within the design process of compressor blades. Some recent studies have shown that the decoupled method considering only the stator disturbances cannot obtain accurate results for cases with strong rotor–stator interactions, especially for the interaction between the rotor and downstream stator, and the coupled method with multi-row configurations is necessary. Factors determine what computational domains to model need to be clarified to find a balance between accuracy requirements and computational costs. To this end, this study conducted full-annulus unsteady calculations with decoupled and coupled configurations to investigate the forced response of an embedded compressor rotor induced by upstream and downstream stator disturbances and rotor–stator interactions, respectively. The results show that the upstream IGV disturbances were dominated by the wake, and the IGV and S1 potential fields had little effect on the R1 response. Meanwhile, the IGV–R1 interactions and S1–R1 interactions were dominated by one cut-on mode, respectively. The comparisons of the blade vibration amplitude and the unsteady pressure field calculated by decoupled and coupled methods revealed the mechanism of the forced response, namely, for the R1 response induced by upstream aerodynamic disturbances, the dominant excitation source was the IGV wake, and the blade vibration amplitude can be predicted by the decoupled method. In terms of the response induced by downstream disturbances, the cut-on S1-R1-interaction mode was dominant and the use of the decoupled method without considering its influence will lead to an inaccurate prediction. This study concluded that the formation process of rotor–stator interactions was the key factor that determines whether the decoupled method or coupled method should be used, and analogized a process independent of the downstream stator disturbance. The results can provide a preliminary configuration for accurate and efficient blade response predictions and explain the reason why including downstream stator vanes is very important.

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Analysis of the Effect of Multirow and Multipassage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration—Part I: Aerodynamic Excitation

Cited by 17 publications

References 21 publications

Accounting for Circumferential Flow Nonuniformity in a Multistage Axial Compressor

Accounting for Circumferential Flow Nonuniformity in a Multistage Axial Compressor

Flutter Analysis of an Embedded Blade Row with a Harmonic Balance Solver

Forced Response Analysis of an Embedded Compressor Rotor Induced by Stator Disturbances and Rotor–Stator Interactions

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