Details
| Original language | English |
|---|---|
| Article number | 051002-1 |
| Number of pages | 7 |
| Journal | Journal of Engineering for Gas Turbines and Power |
| Volume | 142 |
| Issue number | 5 |
| Early online date | 14 Feb 2020 |
| Publication status | Published - May 2020 |
Abstract
The dynamics of turbine blades with underplatform dampers (UPDs) is often experimentally explored by using small test rigs like two-blade models for cost and complexity reasons. In this paper, the dynamics of a large-scale academic turbine disk is measured on a special rotation test rig. Such measurements have rarely been published so far. The test rig supports speeds up to 3600 rpm and turbine disks up to a diameter of 1.2 m. The turbine disk is tested linearly as well as with asymmetric and cylindrical UPDs. The excitation forces and the excitation order are varied. The results prove the damper effectiveness by lowering resonance amplitudes. Additionally, the mistuning influence on the result depiction is discussed. The measurements are compared to simulations of the nonlinear frequency response functions (FRFs), showing good agreement.
ASJC Scopus subject areas
- Engineering(all)
- Mechanical Engineering
- Engineering(all)
- Aerospace Engineering
- Energy(all)
- Energy Engineering and Power Technology
- Energy(all)
- Fuel Technology
- Energy(all)
- Nuclear Energy and Engineering
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In: Journal of Engineering for Gas Turbines and Power, Vol. 142, No. 5, 051002-1, 05.2020.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Measured and Simulated Forced Response of a Rotating Turbine Disk With Asymmetric and Cylindrical Underplatform Dampers
AU - Hoffmann, Thomas
AU - Panning-von Scheidt, Lars
AU - Wallaschek, Jörg
N1 - Funding Information: The investigations were conducted as part of the joint research program COOREFlex-turbo in the frame of AG Turbo. The work was supported by the Bundesministerium fur Wirtschaft und Technologie (BMWi) as per resolution of the German Federal Parliament under grant number 03ET7041 L. The authors
PY - 2020/5
Y1 - 2020/5
N2 - The dynamics of turbine blades with underplatform dampers (UPDs) is often experimentally explored by using small test rigs like two-blade models for cost and complexity reasons. In this paper, the dynamics of a large-scale academic turbine disk is measured on a special rotation test rig. Such measurements have rarely been published so far. The test rig supports speeds up to 3600 rpm and turbine disks up to a diameter of 1.2 m. The turbine disk is tested linearly as well as with asymmetric and cylindrical UPDs. The excitation forces and the excitation order are varied. The results prove the damper effectiveness by lowering resonance amplitudes. Additionally, the mistuning influence on the result depiction is discussed. The measurements are compared to simulations of the nonlinear frequency response functions (FRFs), showing good agreement.
AB - The dynamics of turbine blades with underplatform dampers (UPDs) is often experimentally explored by using small test rigs like two-blade models for cost and complexity reasons. In this paper, the dynamics of a large-scale academic turbine disk is measured on a special rotation test rig. Such measurements have rarely been published so far. The test rig supports speeds up to 3600 rpm and turbine disks up to a diameter of 1.2 m. The turbine disk is tested linearly as well as with asymmetric and cylindrical UPDs. The excitation forces and the excitation order are varied. The results prove the damper effectiveness by lowering resonance amplitudes. Additionally, the mistuning influence on the result depiction is discussed. The measurements are compared to simulations of the nonlinear frequency response functions (FRFs), showing good agreement.
UR - http://www.scopus.com/inward/record.url?scp=85091698108&partnerID=8YFLogxK
U2 - 10.1115/1.4045337
DO - 10.1115/1.4045337
M3 - Article
VL - 142
JO - Journal of Engineering for Gas Turbines and Power
JF - Journal of Engineering for Gas Turbines and Power
SN - 0742-4795
IS - 5
M1 - 051002-1
ER -