TY - JOUR

T1 - Forced Response Due to Vane Stagger Angle Variation in an Axial Compressor

AU - Maroldt, Niklas

AU - Amer, Mona

AU - Seume, Joerg R.

N1 - Funding Information: The present work has been carried out in the subproject C6 within the Collaborative Research Center (CRC) 871 “Regeneration of Complex Capital Goods,” which is funded by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation)—SFB 871/3 - 119193472. The authors kindly thank DFG for the financial support to accomplish this research project. Moreover, the authors would like to acknowledge the substantial contribution of the DLR Institute of Propulsion Technology and MTU Aero Engines AG for providing TRACE.

PY - 2022/8

Y1 - 2022/8

N2 - Recent developments in turbomachinery design require an improved prediction accuracy of blade vibrations to maintain safe operations. This article aims to investigate the accuracy of numerical aeroelastic approaches for the calculation of blade vibrations. For validation, extensive aerodynamic and forced response measurements in an 1.5-stage axial compressor with a blade integrated disk (Blisk) are presented. The excitation intensity of the vibration is controlled by varying the stagger angle of the inlet guide vane (IGV). In addition, a second engine order is imposed by a nonsymmetric circumferential vane angle distribution to simulate a multistage behavior. Experimental validated Reynolds-averaged Navier–Stokes (RANS) simulations in both the frequency and the time domain are compared to assess the prediction accuracy of the numerical approaches. The numerical results agree with the experiments for low and intermediate vane angles. However, at high IGV stagger angles and when exciting multiple engine orders, the inaccuracy in the prediction of flow separation by the RANS simulations leads to an overprediction of vibration amplitudes. This exaggeration becomes even more pronounced in the frequency domain simulations. Time domain methods with a time lag formulation tend to be efficient and more accurate approaches for large separated flow regimes.

AB - Recent developments in turbomachinery design require an improved prediction accuracy of blade vibrations to maintain safe operations. This article aims to investigate the accuracy of numerical aeroelastic approaches for the calculation of blade vibrations. For validation, extensive aerodynamic and forced response measurements in an 1.5-stage axial compressor with a blade integrated disk (Blisk) are presented. The excitation intensity of the vibration is controlled by varying the stagger angle of the inlet guide vane (IGV). In addition, a second engine order is imposed by a nonsymmetric circumferential vane angle distribution to simulate a multistage behavior. Experimental validated Reynolds-averaged Navier–Stokes (RANS) simulations in both the frequency and the time domain are compared to assess the prediction accuracy of the numerical approaches. The numerical results agree with the experiments for low and intermediate vane angles. However, at high IGV stagger angles and when exciting multiple engine orders, the inaccuracy in the prediction of flow separation by the RANS simulations leads to an overprediction of vibration amplitudes. This exaggeration becomes even more pronounced in the frequency domain simulations. Time domain methods with a time lag formulation tend to be efficient and more accurate approaches for large separated flow regimes.

KW - aeromechanical instabilities

KW - compressor

KW - computational fluid dynamics (CFD)

KW - forced response

UR - http://www.scopus.com/inward/record.url?scp=85141359307&partnerID=8YFLogxK

U2 - 10.1115/1.4053839

DO - 10.1115/1.4053839

M3 - Article

AN - SCOPUS:85141359307

VL - 144

JO - Journal of Turbomachinery

JF - Journal of Turbomachinery

SN - 0889-504X

IS - 8

M1 - 081011

ER -