Details
| Original language | English |
|---|---|
| Pages (from-to) | 9-17 |
| Number of pages | 9 |
| Journal | International Journal of Gas Turbine, Propulsion and Power Systems |
| Volume | 15 |
| Issue number | 3 |
| Publication status | Published - Jun 2024 |
Abstract
Experimental investigations of acoustic excitation and noise propagation in turbomachines require specialized rigs with sophisticated instrumentation. As it remains challenging to integrate such measurements into a real engine, sub-scale test rigs are required with acoustically optimized boundary conditions to isolate acoustic sources. Thus, scaling approaches have to be applied to establish similarity. In the present work similarity parameters are derived and methods to geometrically scale machines while maintaining aeroacoustic similarity are proposed. The scaling approach is investigated using a 1.5-stage turbine test rig. Numerical simulations of the original and geometrically scaled rig are performed to validate similarity using both time and frequency domain methods to simulate aerodynamic and aeroacoustic effects. Transient blade pressures and the acoustic fields induced by blade-vane interaction show a good agreement between the two test cases. Aeroacoustic similarity could thus be achieved using the scaling approach presented which allows for better transferability of sub-scale tests.
ASJC Scopus subject areas
- Engineering(all)
- Mechanical Engineering
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In: International Journal of Gas Turbine, Propulsion and Power Systems, Vol. 15, No. 3, 06.2024, p. 9-17.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - On the Aeroacoustic Scaling of Axial Flow Turbines
AU - Lohse, Stefanie
AU - Schuler, Johanna
AU - Fischer, Felix
AU - Seume, Joerg R.
AU - Moreau, Stéphane
N1 - Publisher Copyright: © 2024 Stefanie Lohse, Johanna Schuler, Felix Fischer, Joerg R. Seume and Stéphane Moreau.
PY - 2024/6
Y1 - 2024/6
N2 - Experimental investigations of acoustic excitation and noise propagation in turbomachines require specialized rigs with sophisticated instrumentation. As it remains challenging to integrate such measurements into a real engine, sub-scale test rigs are required with acoustically optimized boundary conditions to isolate acoustic sources. Thus, scaling approaches have to be applied to establish similarity. In the present work similarity parameters are derived and methods to geometrically scale machines while maintaining aeroacoustic similarity are proposed. The scaling approach is investigated using a 1.5-stage turbine test rig. Numerical simulations of the original and geometrically scaled rig are performed to validate similarity using both time and frequency domain methods to simulate aerodynamic and aeroacoustic effects. Transient blade pressures and the acoustic fields induced by blade-vane interaction show a good agreement between the two test cases. Aeroacoustic similarity could thus be achieved using the scaling approach presented which allows for better transferability of sub-scale tests.
AB - Experimental investigations of acoustic excitation and noise propagation in turbomachines require specialized rigs with sophisticated instrumentation. As it remains challenging to integrate such measurements into a real engine, sub-scale test rigs are required with acoustically optimized boundary conditions to isolate acoustic sources. Thus, scaling approaches have to be applied to establish similarity. In the present work similarity parameters are derived and methods to geometrically scale machines while maintaining aeroacoustic similarity are proposed. The scaling approach is investigated using a 1.5-stage turbine test rig. Numerical simulations of the original and geometrically scaled rig are performed to validate similarity using both time and frequency domain methods to simulate aerodynamic and aeroacoustic effects. Transient blade pressures and the acoustic fields induced by blade-vane interaction show a good agreement between the two test cases. Aeroacoustic similarity could thus be achieved using the scaling approach presented which allows for better transferability of sub-scale tests.
UR - http://www.scopus.com/inward/record.url?scp=85199898458&partnerID=8YFLogxK
U2 - 10.38036/jgpp.15.3_9
DO - 10.38036/jgpp.15.3_9
M3 - Article
AN - SCOPUS:85199898458
VL - 15
SP - 9
EP - 17
JO - International Journal of Gas Turbine, Propulsion and Power Systems
JF - International Journal of Gas Turbine, Propulsion and Power Systems
IS - 3
ER -