Kilian, Nicklas ; Klausmann, Fabian ; Spieker, Daniel ; Schiffer, Heinz-Peter ; Salas, Mauricio Gutiérrez (2024)
Numerical Investigation of Forced Response in a Transonic Compressor Stage — Highlighting Challenges Using Experimental Validation.
In: International Journal of Turbomachinery, Propulsion and Power, 2024, 9 (2)
doi: 10.26083/tuprints-00027829
Artikel, Zweitveröffentlichung, Verlagsversion
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Kurzbeschreibung (Abstract)
An experiment-supported simulation process chain is set up to perform numerical forced response analyses on a transonic high-pressure compressor front stage at varying operating conditions. A wake generator is used upstream of the rotor to excite a specific resonance within the operating range of the compressor. Thereby, extensive aerodynamic and structural dynamic experimental data, obtained from state-of-the-art rig testing at the Transonic Compressor Darmstadt test facility at the Technical University of Darmstadt, are used to validate numerical results and ensure realistic boundary conditions. In the course of this, five-hole-probe measurements at steady operating conditions close to the investigated resonance enable a validation of the steady aerodynamics. Subsequently, numerically obtained aeroelastic quantities, such as resonance frequency, and damping, as well as maximum alternating blade stresses and tip deflections, are compared to experimental blade tip timing data. Experimental trends in damping can be confirmed and better explained by considering numerical results regarding the aerodynamic wall work density and secondary flow phenomena. The influence of varying loading conditions on the resonance frequency is not observed as distinctly in numerical, as in experimental results. Generally, alternating blade stresses and deflections appear to be significantly lower than in the experiments. However, similar to the aerodynamic damping, numerical results contribute to a better understanding of experimental trends. The successive experimental validation shows the capabilities of the numerical forced response analysis setup and enables the highlighting of challenges and identification of potential further adaptations.
| Typ des Eintrags: | Artikel |
|---|---|
| Erschienen: | 2024 |
| Autor(en): | Kilian, Nicklas ; Klausmann, Fabian ; Spieker, Daniel ; Schiffer, Heinz-Peter ; Salas, Mauricio Gutiérrez |
| Art des Eintrags: | Zweitveröffentlichung |
| Titel: | Numerical Investigation of Forced Response in a Transonic Compressor Stage — Highlighting Challenges Using Experimental Validation |
| Sprache: | Englisch |
| Publikationsjahr: | 18 September 2024 |
| Ort: | Darmstadt |
| Publikationsdatum der Erstveröffentlichung: | Juni 2024 |
| Ort der Erstveröffentlichung: | Basel |
| Verlag: | MDPI |
| Titel der Zeitschrift, Zeitung oder Schriftenreihe: | International Journal of Turbomachinery, Propulsion and Power |
| Jahrgang/Volume einer Zeitschrift: | 9 |
| (Heft-)Nummer: | 2 |
| Kollation: | 21 Seiten |
| DOI: | 10.26083/tuprints-00027829 |
| URL / URN: | https://tuprints.ulb.tu-darmstadt.de/27829 |
| Zugehörige Links: | |
| Herkunft: | Zweitveröffentlichung DeepGreen |
| Kurzbeschreibung (Abstract): | An experiment-supported simulation process chain is set up to perform numerical forced response analyses on a transonic high-pressure compressor front stage at varying operating conditions. A wake generator is used upstream of the rotor to excite a specific resonance within the operating range of the compressor. Thereby, extensive aerodynamic and structural dynamic experimental data, obtained from state-of-the-art rig testing at the Transonic Compressor Darmstadt test facility at the Technical University of Darmstadt, are used to validate numerical results and ensure realistic boundary conditions. In the course of this, five-hole-probe measurements at steady operating conditions close to the investigated resonance enable a validation of the steady aerodynamics. Subsequently, numerically obtained aeroelastic quantities, such as resonance frequency, and damping, as well as maximum alternating blade stresses and tip deflections, are compared to experimental blade tip timing data. Experimental trends in damping can be confirmed and better explained by considering numerical results regarding the aerodynamic wall work density and secondary flow phenomena. The influence of varying loading conditions on the resonance frequency is not observed as distinctly in numerical, as in experimental results. Generally, alternating blade stresses and deflections appear to be significantly lower than in the experiments. However, similar to the aerodynamic damping, numerical results contribute to a better understanding of experimental trends. The successive experimental validation shows the capabilities of the numerical forced response analysis setup and enables the highlighting of challenges and identification of potential further adaptations. |
| Freie Schlagworte: | axial compressor, transonic, aerodynamics, aeroelasticity, forced response, numerical, experimental |
| ID-Nummer: | Artikel-ID: 22 |
| Status: | Verlagsversion |
| URN: | urn:nbn:de:tuda-tuprints-278293 |
| Zusätzliche Informationen: | This article belongs to the Special Issue Selected Papers from the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT16) This paper is an extended version of our paper published in the Proceedings of the 16th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines, Toledo, Spain, 19–23 September 2022; paper No. 037. |
| Sachgruppe der Dewey Dezimalklassifikatin (DDC): | 600 Technik, Medizin, angewandte Wissenschaften > 620 Ingenieurwissenschaften und Maschinenbau |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet für Gasturbinen, Luft- und Raumfahrtantriebe (GLR) 16 Fachbereich Maschinenbau > Fachgebiet für Gasturbinen, Luft- und Raumfahrtantriebe (GLR) > Verdichter |
| Hinterlegungsdatum: | 18 Sep 2024 11:44 |
| Letzte Änderung: | 19 Sep 2024 05:46 |
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| Suche nach Titel in: | TUfind oder in Google |
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