Details
| Original language | English |
|---|---|
| Title of host publication | Structures and Dynamics - Probabilistic Methods; Rotordynamics; Structural Mechanics and Vibration |
| Publisher | American Society of Mechanical Engineers(ASME) |
| ISBN (electronic) | 9780791886076 |
| Publication status | Published - 2022 |
| Event | ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition, GT 2022 - Rotterdam, Netherlands Duration: 13 Jun 2022 → 17 Jun 2022 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Volume | 8-B |
Abstract
Vibration amplitudes and fatigue life in multistage turbomachinery are commonly estimated by an isolated investigation of the individual stages. Research is currently extending the scope to include inter-stage coupling of structural dynamics and aeroelasticity, i.e. aerodynamic coupling. These two effects have been shown to significantly influence blade vibrations. For safe operation of modern blisk blading with its lower structural damping due to the elimination of frictional contacts at the blade roots, an accurate prediction of the vibration behavior in multistage configurations with mistuning is necessary to avoid high cycle fatigue (HCF) failures. In this paper, a cyclic Craig-Bampton reduction method with a priori interface reduction for multistage rotors is extended to handle aeroelastic effects. These reduced order models efficiently predict forced response in multistage applications. Aeroelastic multistage simulations are carried out using the harmonic balance method to account for the stage interactions and yield damping and stiffness coefficients, as well as modal excitation forces. Small structural mistuning is projected onto the tuned system modes of the rotor. The reduced order approach is applied to a two-stage compressor configuration. Monte Carlo simulations show the sensitivity of vibration amplitudes to the aeroelastic coupling for mistuning. The aeroelastic inter-stage coupling is found to originate mainly from acoustic mode propagation between the rotor stages. The fatigue of rotor blades is significantly affected by multistage interaction since vibration amplitudes increase due to the superposition of the vibration responses of multiple modes. This leads to the conclusion that aeroelastic multistage effects need to be incorporated in future design procedures to allow for an accurate prediction of fatigue life of compressor rotors.
ASJC Scopus subject areas
- Engineering(all)
- General Engineering
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Structures and Dynamics - Probabilistic Methods; Rotordynamics; Structural Mechanics and Vibration. American Society of Mechanical Engineers(ASME), 2022. V08BT27A007 (Proceedings of the ASME Turbo Expo; Vol. 8-B).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Reduced Order Modeling of Forced Response in a Multistage Compressor Under Mistuning and Aerocoupling
AU - Maroldt, Niklas
AU - Seume, Joerg R.
AU - Schwerdt, Lukas
AU - Panning-von Scheidt, Lars
AU - Wallaschek, Jörg
AU - Berger, Ricarda
AU - Rolfes, Raimund
N1 - Funding Information: The authors gratefully acknowledge the funding of the present work through CRC 871 “Regeneration of Complex Capital Goods”, funded by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation) – SFB 871/3 – 119193472. 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
Y1 - 2022
N2 - Vibration amplitudes and fatigue life in multistage turbomachinery are commonly estimated by an isolated investigation of the individual stages. Research is currently extending the scope to include inter-stage coupling of structural dynamics and aeroelasticity, i.e. aerodynamic coupling. These two effects have been shown to significantly influence blade vibrations. For safe operation of modern blisk blading with its lower structural damping due to the elimination of frictional contacts at the blade roots, an accurate prediction of the vibration behavior in multistage configurations with mistuning is necessary to avoid high cycle fatigue (HCF) failures. In this paper, a cyclic Craig-Bampton reduction method with a priori interface reduction for multistage rotors is extended to handle aeroelastic effects. These reduced order models efficiently predict forced response in multistage applications. Aeroelastic multistage simulations are carried out using the harmonic balance method to account for the stage interactions and yield damping and stiffness coefficients, as well as modal excitation forces. Small structural mistuning is projected onto the tuned system modes of the rotor. The reduced order approach is applied to a two-stage compressor configuration. Monte Carlo simulations show the sensitivity of vibration amplitudes to the aeroelastic coupling for mistuning. The aeroelastic inter-stage coupling is found to originate mainly from acoustic mode propagation between the rotor stages. The fatigue of rotor blades is significantly affected by multistage interaction since vibration amplitudes increase due to the superposition of the vibration responses of multiple modes. This leads to the conclusion that aeroelastic multistage effects need to be incorporated in future design procedures to allow for an accurate prediction of fatigue life of compressor rotors.
AB - Vibration amplitudes and fatigue life in multistage turbomachinery are commonly estimated by an isolated investigation of the individual stages. Research is currently extending the scope to include inter-stage coupling of structural dynamics and aeroelasticity, i.e. aerodynamic coupling. These two effects have been shown to significantly influence blade vibrations. For safe operation of modern blisk blading with its lower structural damping due to the elimination of frictional contacts at the blade roots, an accurate prediction of the vibration behavior in multistage configurations with mistuning is necessary to avoid high cycle fatigue (HCF) failures. In this paper, a cyclic Craig-Bampton reduction method with a priori interface reduction for multistage rotors is extended to handle aeroelastic effects. These reduced order models efficiently predict forced response in multistage applications. Aeroelastic multistage simulations are carried out using the harmonic balance method to account for the stage interactions and yield damping and stiffness coefficients, as well as modal excitation forces. Small structural mistuning is projected onto the tuned system modes of the rotor. The reduced order approach is applied to a two-stage compressor configuration. Monte Carlo simulations show the sensitivity of vibration amplitudes to the aeroelastic coupling for mistuning. The aeroelastic inter-stage coupling is found to originate mainly from acoustic mode propagation between the rotor stages. The fatigue of rotor blades is significantly affected by multistage interaction since vibration amplitudes increase due to the superposition of the vibration responses of multiple modes. This leads to the conclusion that aeroelastic multistage effects need to be incorporated in future design procedures to allow for an accurate prediction of fatigue life of compressor rotors.
UR - http://www.scopus.com/inward/record.url?scp=85141433077&partnerID=8YFLogxK
U2 - 10.1115/GT2022-81090
DO - 10.1115/GT2022-81090
M3 - Conference contribution
AN - SCOPUS:85141433077
T3 - Proceedings of the ASME Turbo Expo
BT - Structures and Dynamics - Probabilistic Methods; Rotordynamics; Structural Mechanics and Vibration
PB - American Society of Mechanical Engineers(ASME)
T2 - ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition, GT 2022
Y2 - 13 June 2022 through 17 June 2022
ER -