Representation and Analysis of Geometric Uncertainties in Rotor Blades

Carassale, Luigi; Bruzzone, Silvia; Cavicchi, Andrea; Brunenghi, Michela Marré

doi:10.1115/gt2018-76385

Cited by 4 publications

(6 citation statements)

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“…The point cloud representing the measured geometry of the real one-piece component is used to construct the detailed FEM of the blended blisk. In previous research efforts [15,16], the mesh morphing strategies proved to be viable and valuable tools for semi-automatically generating a high-fidelity FEM directly from the blisk point cloud. In contrast, the classical reverse engineering method tends to be timeconsuming and less efficient because the point cloud data should be first processed into a CAD model to obtain the volumes, which are then meshed into a FEM.…”

Section: Geometry Measurement By Three-dimensional Opticalmentioning

confidence: 99%

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Blisk With Small Geometry Mistuning and Blend Repair: As-Measured Finite Element Model and Experimental Verification

Zhou

Zhao

et al. 2022

Journal of Engineering for Gas Turbines and Power

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This paper presents an 'As-Measured Model' of a blended blisk, built upon the measurement of the true geometry of the blisk by the 3D optical scanning technology. This high-fidelity model aims to account for the variances of blade frequencies and mode shapes within the real blisk in the presence of both the blend repair and inherent geometry mistuning due to manufacturing, etc. An improved mesh updating strategy is proposed to adapt a seed blisk finite element model to the measured geometry. The resultant 'as-measured model' is therefore able to accurately represent the measured blade-to-blade geometry variances. The classical blade detuning test in combination with a novel 'correction' procedure is employed to experimentally evaluate the 'blade-alone' frequency mistuning pattern in the real blisk. Experimental verification of the 'as-measured model' demonstrates that it is able to not only capture the 'blade-alone' frequency and mode shape variations due to both the blend and intrinsic blade geometry variances, but also to reproduce the global dynamics of the blended blisk with acceptable accuracy.

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Section: Geometry Measurement By Three-dimensional Opticalmentioning

confidence: 99%

“…Therefore, blade geometric features could be explicitly modeled in the resultant as-manufactured model [14]. The updating process can be realized by specifically developed mesh morphing algorithms [15,16] provided that the measured point cloud slightly deviates from the nominal FEM.…”

Section: Introductionmentioning

confidence: 99%

Blisk With Small Geometry Mistuning and Blend Repair: As-Measured Finite Element Model and Experimental Verification

Zhou

Zhao

et al. 2022

Journal of Engineering for Gas Turbines and Power

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“…Over the past decades, many efforts have been devoted to the uncertainty quantification (UQ) of the aerodynamic performance of axial compressors (Carassale et al, 2018;Seshadri et al, 2015;Qin et al, 2016;Wunsch et al, 2015). However, few revelant studies have been conducted on centrifugal compressors in the open literature.…”

Section: Introductionmentioning

confidence: 99%

Effects of Geometric and Operational Uncertainties on the Aerodynamic Performance of a Centrifugal Compressor Stage

Zhu¹,

Ju²,

Zhang³

2022

Proceedings of Global Power &Amp; Propulsion Society

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No real centrifugal compressor performance exactly conforms to its design geometry and expected operating conditions due to the uncertainties existing in the manufacturing and in-service process. The compressor performance can be adversely affected by such uncertainties and performs instability. However, relevant studies concerning geometric and operational uncertainties simultaneously are quite rare, and the underlying flow mechanism even remains unknown. Here we present both deterministic and uncertainty analysis of a centrifugal compressor stage with considering geometric and operational uncertainties simultaneously. With the combination of CFD simulation and nonintrusive sparse grid based stochastic collocation methods, the combined and single effects of total inlet temperature, total inlet pressure, outlet mass flow, impeller tip clearance and hub fillet radius on the stage/impeller performance are quantified and analysed. The results show that these uncertainties exert more influence on stage rather than impeller performance, therein the uncertain tip clearance contributes the most. To investigate such declined performance indeed, the flow field was then uncovered. It is demonstrated that the wake of tip clearance produces distorted flow downstream towards the diffuser, which causes complicated vortex structures. This present study lays a theoretical foundation to provide guidelines for developing a robust design of centrifugal compressor.

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“…Carassale et al. 8 analysed the effect of the uncertain geometry of the blade surface on the rotor blade natural frequencies in realistic applications. Loeven et al.…”

Section: Introductionmentioning

confidence: 99%

“…For example, Garzon and Darmofal [5][6][7] performed an uncertainty analysis on the aerodynamic performance of an axial compressor under geometric uncertainties due to the manufacturing process. Carassale et al 8 analysed the effect of the uncertain geometry of the blade surface on the rotor blade natural frequencies in realistic applications. Loeven et al 9 studied the effect of the uncertain inlet total pressure profile on the aerodynamic performance of an axial compressor rotor.…”

Section: Introductionmentioning

confidence: 99%

Effects of geometric and operational uncertainties on aerodynamic performance of centrifugal compressor stage

Zhu

Zhang

2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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No real centrifugal compressor can exactly conform to its design geometry and expected operating conditions due to the uncertainties existing in the manufacturing and operational processes. Such uncertainties have been increasingly recognised to be detrimental to compressor performance. However, quite few studies have focused on the combined effects of geometric and operational uncertainties on compressor performance, and the underlying flow mechanism even remains unclear. In this context, we here present an uncertainty analysis of a centrifugal compressor stage, with both geometric and operational uncertainties taken into account. With the combination of CFD simulation and nonintrusive sparse grid based stochastic collocation methods, the combined and individual effects of total inlet temperature, total inlet pressure, outlet mass flow, impeller tip clearance and hub fillet radius on the stage/impeller performance are quantified and analysed. Particular attention is paid to elucidating the compressor performance variations through flow field and energy decomposition analyses. Results show that the considered uncertainties exert more influence on the compressor stage performance rather than on the impeller performance. Amongst the examined uncertainties, the impeller tip clearance contributes the most to the stage performance. The underlying mechanism lies in that the wake of impeller tip clearance produces distorted flow downstream towards the diffuser, which causes complicated vortex structures and less conversion of kinetic energy to pressure rise in the diffuser passage. The present study lays a theoretical foundation for the further uncertainty quantification and robust design of centrifugal compressors against various sources of uncertainties.

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Representation and Analysis of Geometric Uncertainties in Rotor Blades

Cited by 4 publications

References 0 publications

Blisk With Small Geometry Mistuning and Blend Repair: As-Measured Finite Element Model and Experimental Verification

Blisk With Small Geometry Mistuning and Blend Repair: As-Measured Finite Element Model and Experimental Verification

Effects of Geometric and Operational Uncertainties on the Aerodynamic Performance of a Centrifugal Compressor Stage

Effects of geometric and operational uncertainties on aerodynamic performance of centrifugal compressor stage

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