Details
| Original language | English |
|---|---|
| Article number | 051005 |
| Number of pages | 9 |
| Journal | Journal of Engineering for Gas Turbines and Power |
| Volume | 143 |
| Issue number | 5 |
| Early online date | 11 Mar 2021 |
| Publication status | Published - May 2021 |
Abstract
This article addresses the vibrational behavior of bladed disk assemblies with nonlinear shroud coupling under random excitation. In order to increase the service life and safety of turbine blades, intense calculations are carried out to predict the vibrational behavior. The use of friction dampers for energy dissipation and suppression of large amplitudes makes the mechanical system nonlinear, which complicates the calculations. Depending on the stage, different types of excitation can occur in a turbine, from clearly defined deterministic to random excitation. So far, the latter problem has only been dealt with to a limited extent in the literature on turbomachinery. Nevertheless, there are in general different approaches and methods to address this problem most of which are strongly restricted with regard to the number of degrees-of-freedom (DOF). The focus of this paper is the application of an equivalent linearization method (ELM) to calculate the stochastic response of an academic model of a bladed disk assembly under random excitation. The nonlinear contact is modeled both with an elastic Coulomb-slider and a Bouc-Wen formulation to reproduce the hysteretic character of a friction nonlinearity occurring in the presence of a friction damper. Both the excitation and the response are limited to mean-free, stationary stochastic processes, which means that the stochastic moments do not change over time. Unlike previous papers on this topic, the calculations are performed on a full bladed disk assembly in which each segment is approximated with several degrees-of-freedom.
ASJC Scopus subject areas
- Energy(all)
- Nuclear Energy and Engineering
- Energy(all)
- Fuel Technology
- Engineering(all)
- Aerospace Engineering
- Energy(all)
- Energy Engineering and Power Technology
- Engineering(all)
- Mechanical Engineering
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In: Journal of Engineering for Gas Turbines and Power, Vol. 143, No. 5, 051005, 05.2021.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Equivalent Linearization of Bladed Disk Assemblies With Friction Nonlinearities Under Random Excitation
AU - Förster, Alwin
AU - Panning-von Scheidt, Lars
AU - Wallaschek, Jörg
N1 - Funding Information: The investigations were conducted as part of the joint research program SchauTex in the frame of AG Turbo. The work was supported by the Bundesministerium fur Wirtschaft und Energie (BMWi) as per resolution of the German Bundestag under Grant No. 03424292D. The authors gratefully acknowledge MAN Energy Solutions, MTU Aero Engines and Siemens Gas and Power for their support and permission to publish this paper. The responsibility for the content lies solely with its authors.
PY - 2021/5
Y1 - 2021/5
N2 - This article addresses the vibrational behavior of bladed disk assemblies with nonlinear shroud coupling under random excitation. In order to increase the service life and safety of turbine blades, intense calculations are carried out to predict the vibrational behavior. The use of friction dampers for energy dissipation and suppression of large amplitudes makes the mechanical system nonlinear, which complicates the calculations. Depending on the stage, different types of excitation can occur in a turbine, from clearly defined deterministic to random excitation. So far, the latter problem has only been dealt with to a limited extent in the literature on turbomachinery. Nevertheless, there are in general different approaches and methods to address this problem most of which are strongly restricted with regard to the number of degrees-of-freedom (DOF). The focus of this paper is the application of an equivalent linearization method (ELM) to calculate the stochastic response of an academic model of a bladed disk assembly under random excitation. The nonlinear contact is modeled both with an elastic Coulomb-slider and a Bouc-Wen formulation to reproduce the hysteretic character of a friction nonlinearity occurring in the presence of a friction damper. Both the excitation and the response are limited to mean-free, stationary stochastic processes, which means that the stochastic moments do not change over time. Unlike previous papers on this topic, the calculations are performed on a full bladed disk assembly in which each segment is approximated with several degrees-of-freedom.
AB - This article addresses the vibrational behavior of bladed disk assemblies with nonlinear shroud coupling under random excitation. In order to increase the service life and safety of turbine blades, intense calculations are carried out to predict the vibrational behavior. The use of friction dampers for energy dissipation and suppression of large amplitudes makes the mechanical system nonlinear, which complicates the calculations. Depending on the stage, different types of excitation can occur in a turbine, from clearly defined deterministic to random excitation. So far, the latter problem has only been dealt with to a limited extent in the literature on turbomachinery. Nevertheless, there are in general different approaches and methods to address this problem most of which are strongly restricted with regard to the number of degrees-of-freedom (DOF). The focus of this paper is the application of an equivalent linearization method (ELM) to calculate the stochastic response of an academic model of a bladed disk assembly under random excitation. The nonlinear contact is modeled both with an elastic Coulomb-slider and a Bouc-Wen formulation to reproduce the hysteretic character of a friction nonlinearity occurring in the presence of a friction damper. Both the excitation and the response are limited to mean-free, stationary stochastic processes, which means that the stochastic moments do not change over time. Unlike previous papers on this topic, the calculations are performed on a full bladed disk assembly in which each segment is approximated with several degrees-of-freedom.
UR - http://www.scopus.com/inward/record.url?scp=85107567702&partnerID=8YFLogxK
U2 - 10.1115/1.4048407
DO - 10.1115/1.4048407
M3 - Article
VL - 143
JO - Journal of Engineering for Gas Turbines and Power
JF - Journal of Engineering for Gas Turbines and Power
SN - 0742-4795
IS - 5
M1 - 051005
ER -