Details
| Original language | English |
|---|---|
| Title of host publication | AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials |
| Publisher | American Institute of Aeronautics and Astronautics Inc. (AIAA) |
| Edition | 210049 |
| ISBN (print) | 9781624105326 |
| Publication status | Published - 7 Jan 2018 |
| Event | AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018 - Kissimmee, United States Duration: 8 Jan 2018 → 12 Jan 2018 |
Publication series
| Name | AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018 |
|---|---|
| Number | 210049 |
Abstract
A major concern in the design process of modern turbomachinery, e.g. aircraft engines, is aeroelasticity. Due to the possible risk of failure of the aircraft engine by cause of highcycle fatigue (HCF), numerical analyses for the estimation of utter and forced response risk are already carried out during the design phase. Therefore, the validation of the aeroelastic toolchain used is an important prerequisit of the design. This paper shows a validation of time-linearized forced response CFD results created with the CFD code TRACE by a comparison with experimental data. The experimental data is collected out on the 1-stage axial compressor test rig at the Institute of Turbomachinery and Fluid Dynamics at the Leibniz Universität Hannover. The amplitude of the blade oscillation is measured with a commercial tip timing system and subsequently compared with the amplitudes of the numerical forced response calculations. The results of the experimental investigations validate the results of the numerical setup for both investigated mode shapes.
ASJC Scopus subject areas
- Engineering(all)
- Civil and Structural Engineering
- Engineering(all)
- Building and Construction
- Engineering(all)
- Mechanics of Materials
- Engineering(all)
- Architecture
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AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials. 210049. ed. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2018. (AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018; No. 210049).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Experimental Validation of a Forced Response Analysis Using a Time-Linearized Method
AU - Bittner, S.L.
AU - Keller, C.
AU - Meinzer, C.E.
AU - Seume, J.R.
N1 - Publisher Copyright: © 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018/1/7
Y1 - 2018/1/7
N2 - A major concern in the design process of modern turbomachinery, e.g. aircraft engines, is aeroelasticity. Due to the possible risk of failure of the aircraft engine by cause of highcycle fatigue (HCF), numerical analyses for the estimation of utter and forced response risk are already carried out during the design phase. Therefore, the validation of the aeroelastic toolchain used is an important prerequisit of the design. This paper shows a validation of time-linearized forced response CFD results created with the CFD code TRACE by a comparison with experimental data. The experimental data is collected out on the 1-stage axial compressor test rig at the Institute of Turbomachinery and Fluid Dynamics at the Leibniz Universität Hannover. The amplitude of the blade oscillation is measured with a commercial tip timing system and subsequently compared with the amplitudes of the numerical forced response calculations. The results of the experimental investigations validate the results of the numerical setup for both investigated mode shapes.
AB - A major concern in the design process of modern turbomachinery, e.g. aircraft engines, is aeroelasticity. Due to the possible risk of failure of the aircraft engine by cause of highcycle fatigue (HCF), numerical analyses for the estimation of utter and forced response risk are already carried out during the design phase. Therefore, the validation of the aeroelastic toolchain used is an important prerequisit of the design. This paper shows a validation of time-linearized forced response CFD results created with the CFD code TRACE by a comparison with experimental data. The experimental data is collected out on the 1-stage axial compressor test rig at the Institute of Turbomachinery and Fluid Dynamics at the Leibniz Universität Hannover. The amplitude of the blade oscillation is measured with a commercial tip timing system and subsequently compared with the amplitudes of the numerical forced response calculations. The results of the experimental investigations validate the results of the numerical setup for both investigated mode shapes.
UR - http://www.scopus.com/inward/record.url?scp=85044589854&partnerID=8YFLogxK
U2 - 10.2514/6.2018-0461
DO - 10.2514/6.2018-0461
M3 - Conference contribution
SN - 9781624105326
T3 - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018
BT - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials
PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)
T2 - AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -