Details
| Original language | English |
|---|---|
| Title of host publication | AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023 |
| Publisher | American Institute of Aeronautics and Astronautics Inc. (AIAA) |
| Number of pages | 13 |
| ISBN (print) | 9781624107047 |
| Publication status | Published - 8 Jun 2023 |
| Event | AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023 - San Diego, United States Duration: 12 Jun 2023 → 16 Jun 2023 |
Abstract
The main focus of the present work is to discuss an aeroacoustic scaling approach that ensures both aerodynamic and aeroacoustic similarity between a given test rig and an engine. For this purpose, a stator vane row of a four-stage high-speed axial compressor (4AC) based on the test rig at the Institute of Turbomachinery and Fluid Dynamics (TFD) at Leibniz University Hannover is scaled to fit into the TFD’s Aeroacoustic Wind Tunnel (AWT). A numerical investigation based on multiple modelling approaches is performed to verify a similar aeroacoustic behaviour in both test rigs. Reynolds-averaged Navier-Stokes (RANS) simulations are carried out to assess the aerodynamic characteristics of the vane rows. The aeroacoustic modelling consists of unsteady harmonic balance simulations with a single passage setup and an upstream excitation to account for the rotor-stator interaction and the occurrence of scattered frequencies or acoustic modes. The CFD results show that aerodynamic similarity was achieved over a wide operating range. Moreover, the CAA results indicate that the modal transmission behaviour of the vane row could be matched reasonably well for both test rigs. The resulting numerically validated aeroacoustic scaling approach can be used to reduce the experimental effort for aeroacoustic measurements in turbomachinery.
ASJC Scopus subject areas
- Energy(all)
- Energy Engineering and Power Technology
- Energy(all)
- Nuclear Energy and Engineering
- Engineering(all)
- Aerospace Engineering
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AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023. American Institute of Aeronautics and Astronautics Inc. (AIAA), 2023.
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Numerical Validation of an Aeroacoustic Scaling Approach
AU - Lohse, Stefanie
AU - Seume, Joerg R.
AU - Moreau, Stéphane
N1 - Publisher Copyright: © 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023/6/8
Y1 - 2023/6/8
N2 - The main focus of the present work is to discuss an aeroacoustic scaling approach that ensures both aerodynamic and aeroacoustic similarity between a given test rig and an engine. For this purpose, a stator vane row of a four-stage high-speed axial compressor (4AC) based on the test rig at the Institute of Turbomachinery and Fluid Dynamics (TFD) at Leibniz University Hannover is scaled to fit into the TFD’s Aeroacoustic Wind Tunnel (AWT). A numerical investigation based on multiple modelling approaches is performed to verify a similar aeroacoustic behaviour in both test rigs. Reynolds-averaged Navier-Stokes (RANS) simulations are carried out to assess the aerodynamic characteristics of the vane rows. The aeroacoustic modelling consists of unsteady harmonic balance simulations with a single passage setup and an upstream excitation to account for the rotor-stator interaction and the occurrence of scattered frequencies or acoustic modes. The CFD results show that aerodynamic similarity was achieved over a wide operating range. Moreover, the CAA results indicate that the modal transmission behaviour of the vane row could be matched reasonably well for both test rigs. The resulting numerically validated aeroacoustic scaling approach can be used to reduce the experimental effort for aeroacoustic measurements in turbomachinery.
AB - The main focus of the present work is to discuss an aeroacoustic scaling approach that ensures both aerodynamic and aeroacoustic similarity between a given test rig and an engine. For this purpose, a stator vane row of a four-stage high-speed axial compressor (4AC) based on the test rig at the Institute of Turbomachinery and Fluid Dynamics (TFD) at Leibniz University Hannover is scaled to fit into the TFD’s Aeroacoustic Wind Tunnel (AWT). A numerical investigation based on multiple modelling approaches is performed to verify a similar aeroacoustic behaviour in both test rigs. Reynolds-averaged Navier-Stokes (RANS) simulations are carried out to assess the aerodynamic characteristics of the vane rows. The aeroacoustic modelling consists of unsteady harmonic balance simulations with a single passage setup and an upstream excitation to account for the rotor-stator interaction and the occurrence of scattered frequencies or acoustic modes. The CFD results show that aerodynamic similarity was achieved over a wide operating range. Moreover, the CAA results indicate that the modal transmission behaviour of the vane row could be matched reasonably well for both test rigs. The resulting numerically validated aeroacoustic scaling approach can be used to reduce the experimental effort for aeroacoustic measurements in turbomachinery.
UR - http://www.scopus.com/inward/record.url?scp=85199870585&partnerID=8YFLogxK
U2 - 10.2514/6.2023-3837
DO - 10.2514/6.2023-3837
M3 - Conference contribution
AN - SCOPUS:85199870585
SN - 9781624107047
BT - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
PB - American Institute of Aeronautics and Astronautics Inc. (AIAA)
T2 - AIAA Aviation and Aeronautics Forum and Exposition, AIAA AVIATION Forum 2023
Y2 - 12 June 2023 through 16 June 2023
ER -