Details
| Originalsprache | Englisch |
|---|---|
| Titel des Sammelwerks | Structures and Dynamics |
| Herausgeber (Verlag) | American Society of Mechanical Engineers(ASME) |
| ISBN (Print) | 9780791851159 |
| Publikationsstatus | Veröffentlicht - 30 Aug. 2018 |
| Veranstaltung | ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018 - Oslo, Norwegen Dauer: 11 Juni 2018 → 15 Juni 2018 |
Publikationsreihe
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Band | 7C |
Abstract
Depending on the in service condition of jet engines, turbine blades may have to be replaced, refurbished, or repaired in the course of an engine overhaul. Thus, significant changes of the turbine blade geometry can be introduced due to regeneration and overhaul processes. Such geometric variances can affect the aerodynamic and aeroelastic behavior of turbine blades. One goal in the development of the regeneration process is to estimate the aerodynamic excitation of turbine blades depending on these geometric variances caused during the regeneration. Therefore, this study presents an experimentally validated comparison of two methods for the prediction of forced response in a multistage axial turbine. Two unidirectional fluid structure interaction (FSI) methods, a time-linearized and a time-accurate with a subsequent linear harmonic analysis, are employed and the results validated against experimental data. The results show that the vibration amplitude of the time-linearized method is in good agreement with the experimental data and, also requires lower computational time than the time-accurate FSI. Based on this result, the time-linearized method is used to perform a sensitivity study of the tip clearance size of the last rotor blade row of the five stage axial turbine. The results show that an increasing tip clearances size causes an up to 1.35 higher vibration amplitude compared to the reference case, due to increased forcing and decreased damping work.
ASJC Scopus Sachgebiete
- Ingenieurwesen (insg.)
- Allgemeiner Maschinenbau
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Structures and Dynamics. American Society of Mechanical Engineers(ASME), 2018. (Proceedings of the ASME Turbo Expo; Band 7C).
Publikation: Beitrag in Buch/Bericht/Sammelwerk/Konferenzband › Aufsatz in Konferenzband › Forschung › Peer-Review
}
TY - GEN
T1 - Experimental validation of forced response methods in a multi-stage axial turbine
AU - Hauptmann, Thomas
AU - Meinzer, Christopher E.
AU - Seume, Joerg R.
N1 - Funding information: The authors kindly thank the German Research Foundation (DFG) for the financial support of the Collaborative Research Center (SFB) 871 “Regeneration of Complex Capital Goods” and the subproject C4 “Regeneration-induced Variance of Aeroelastic Properties of Turbine Blades”. Furthermore, the authors thank the DLR Institute of Propulsion Technology for providing TRACE, ANSYS for providing CFX in an academic license and the Leibniz Universität Hannover IT Services (LUIS) for the computational resources provided.
PY - 2018/8/30
Y1 - 2018/8/30
N2 - Depending on the in service condition of jet engines, turbine blades may have to be replaced, refurbished, or repaired in the course of an engine overhaul. Thus, significant changes of the turbine blade geometry can be introduced due to regeneration and overhaul processes. Such geometric variances can affect the aerodynamic and aeroelastic behavior of turbine blades. One goal in the development of the regeneration process is to estimate the aerodynamic excitation of turbine blades depending on these geometric variances caused during the regeneration. Therefore, this study presents an experimentally validated comparison of two methods for the prediction of forced response in a multistage axial turbine. Two unidirectional fluid structure interaction (FSI) methods, a time-linearized and a time-accurate with a subsequent linear harmonic analysis, are employed and the results validated against experimental data. The results show that the vibration amplitude of the time-linearized method is in good agreement with the experimental data and, also requires lower computational time than the time-accurate FSI. Based on this result, the time-linearized method is used to perform a sensitivity study of the tip clearance size of the last rotor blade row of the five stage axial turbine. The results show that an increasing tip clearances size causes an up to 1.35 higher vibration amplitude compared to the reference case, due to increased forcing and decreased damping work.
AB - Depending on the in service condition of jet engines, turbine blades may have to be replaced, refurbished, or repaired in the course of an engine overhaul. Thus, significant changes of the turbine blade geometry can be introduced due to regeneration and overhaul processes. Such geometric variances can affect the aerodynamic and aeroelastic behavior of turbine blades. One goal in the development of the regeneration process is to estimate the aerodynamic excitation of turbine blades depending on these geometric variances caused during the regeneration. Therefore, this study presents an experimentally validated comparison of two methods for the prediction of forced response in a multistage axial turbine. Two unidirectional fluid structure interaction (FSI) methods, a time-linearized and a time-accurate with a subsequent linear harmonic analysis, are employed and the results validated against experimental data. The results show that the vibration amplitude of the time-linearized method is in good agreement with the experimental data and, also requires lower computational time than the time-accurate FSI. Based on this result, the time-linearized method is used to perform a sensitivity study of the tip clearance size of the last rotor blade row of the five stage axial turbine. The results show that an increasing tip clearances size causes an up to 1.35 higher vibration amplitude compared to the reference case, due to increased forcing and decreased damping work.
UR - http://www.scopus.com/inward/record.url?scp=85054007678&partnerID=8YFLogxK
U2 - 10.1115/GT2018-75390
DO - 10.1115/GT2018-75390
M3 - Conference contribution
AN - SCOPUS:85054007678
SN - 9780791851159
T3 - Proceedings of the ASME Turbo Expo
BT - Structures and Dynamics
PB - American Society of Mechanical Engineers(ASME)
T2 - ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition, GT 2018
Y2 - 11 June 2018 through 15 June 2018
ER -