Forced Response Analysis of a Highly-Loaded Low-Pressure Compressor Stage With Inlet Distortions

Toracchio, Riccardo; Stapelfeldt, Sina; Hillewaert, Koen; Fontaneto, Fabrizio

doi:10.1115/gt2023-103881

Request a copy

Paper published in a book (Scientific congresses and symposiums)

Forced Response Analysis of a Highly-Loaded Low-Pressure Compressor Stage With Inlet Distortions

Toracchio, Riccardo; Stapelfeldt, Sina; Hillewaert, Koen et al.

2023 • In Structures and Dynamics — Aerodynamics Excitation and Damping; Bearing and Seal Dynamics

Peer reviewed

Permalink
https://hdl.handle.net/2268/307508

DOI
10.1115/gt2023-103881

Files (1)Send to Details Statistics Bibliography Similar publications

Files

Full Text

GT2023-103881.pdf

Author postprint (9.83 MB)

Request a copy

All documents in ORBi are protected by a user license.

Send to

RIS BibTex APA Chicago Permalink X Linkedin

Details

Keywords :

Compressor; Distortion; NLH; Flutter; Forced-response

Abstract :

[en] Abstract Due to modern evolutions in propulsion, in view of obtaining higher propulsive efficiency, turbofan engines are subjected to ever higher inlet flow distortions. In these systems, structural damage can be induced by distortion patterns with excitation close to the blade natural frequency. To fill the gap currently present in literature about the impact of inlet distortions on the aeroelastic behaviour of engine components, this paper presents an aerodynamic damping and forced-response analysis on a highly-loaded axial compressor subjected to intake total pressure distortions. First, a stability analysis for the vibrational mode with natural frequency close to the resonance condition at the nominal speed of the machine is performed. Blade deformations are then computed through a distortion induced forced-response analysis at different distortion amplitudes. This work aims at studying the aeromechanical behaviour of a modern compressor, highlighting that the amplitude of the blade vibration does not increase linearly with the distortion amplitude.

Disciplines :

Mechanical engineering

Author, co-author :

Toracchio, Riccardo ; Université de Liège - ULiège > Aérospatiale et Mécanique (A&M) ; von Karman Institute for Fluid Dynamics , Rhode-St-Genèse, Belgium

Stapelfeldt, Sina; Imperial College London , London, Londonshire, United Kingdom

Hillewaert, Koen ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Design of Turbomachines

Fontaneto, Fabrizio; VKI - Von Karman Institute for Fluid Dynamics [BE] > Turbomachinery and Propulsion Department

Language :

English

Title :

Forced Response Analysis of a Highly-Loaded Low-Pressure Compressor Stage With Inlet Distortions

Publication date :

26 June 2023

Event name :

ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition

Event organizer :

American Society of Mechanical Engineers

Event place :

Boston, United States

Event date :

26 June 2023

Audience :

International

Main work title :

Structures and Dynamics — Aerodynamics Excitation and Damping; Bearing and Seal Dynamics

Publisher :

American Society of Mechanical Engineers, New York, United States

Peer reviewed :

Peer reviewed

Additional URL :

https://asmedigitalcollection.asme.org/GT/proceedings-pdf/doi/10.1115/GT2023-103881/7045179/v11at21a017-gt2023-103881.pdf

Available on ORBi :

since 06 October 2023

Statistics

Number of views

13 (3 by ULiège)

Number of downloads

0 (0 by ULiège)

More statistics

Scopus citations^®

Scopus citations^®
without self-citations

OpenCitations

Bibliography

Hall, C.A., Schwartz, E. and Hileman, J.I. “Assessment of Technologies for the Silent Aircraft Initiative.” Journal of PropulsionandPowerVol.25No.6(2009): pp.1153–1162.
Plas, A.P., Sargeant, M.A., Madani, V., Chricton, D., Greitzer, E.M., Hynes, T.P. and Hall, C.A. “Performance of a Boundary Layer Ingesting (BLI) Propulsion System.” 45th AIAA Aerospace Sciences Meeting and Exhibit. 2007.
Uranga, A., Drela, M., Greitzer, E.M., Hall, D.K., Titchener, N.A., Lieu, M.K., Siu, N.M., Casses, C., Huang, A.C., Gatlin, G.M. and Hannon, J.A. “Boundary Layer Ingestion Benefit of the D8 Transport Aircraft.” AIAA Journal Vol. 55 No. 11 (2017): pp. 3693–3708.
Waters, M.H. and Schairer, E.T. “Analysis of Turbofan Propulsion System Weight and Dimensions.” Technical Report No. NASA-TM-X-73199, A-6890. NASA Ames Research Center, CA, US. 1977.
Gunn, E.J. and Hall, C.A. “Aerodynamics of Boundary Layer Ingesting Fans.” Proceedings of ASME Turbo Expo. GT2014-26142. 2014.
Peters, A., Spakovszky, Z.S., Lord, W.K. and Rose, B. “Ultrashort Nacelles for Low Fan Pressure Ratio Propulsors.” Journal of Turbomachinery Vol. 137 No. 2 (2015): p. 14p.
Longley, J.P. and Greitzer, E.M. “Inlet Distortion Effects in Aircraft Propulsion System Integration.” AGARD. Steady and Transient Performance Prediction of Gas Turbine Engines. 1992.
Ryman, J.F., O’Brien, W.F. and Rabe, D.C. “Multi-stage Fan and Compressor Transfer of Inlet Total Pressure Distortion with Emphasis on High Cycle Fatigue.” 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. p. 4979. 2003.
Hamed, A. and Numbers, K. “Inlet Distortion Considerations for High Cycle Fatigue in Gas Turbine Engine.” 33rd AIAA Joint Propulsion Conference and Exhibit. AIAA 1997-336. 1997.
Danforth, C.E. “Distortion-Induced Vibration in Fan and Compressor Blading.” Journal of Aircraft Vol. 12 No. 4 (1975): pp. 216–225.
Fleeter, S. “Aeroelasticity Research for Turbomachine Applications.” Journal of Aircraft Vol. 16 No. 5 (1979): pp. 320–326.
Zhang, Y., Pan, J.,, Zhu, Y., Dong, X. and Luo, J. “Investigation of the Flutter Stability of a Transonic Fan with Inlet Distortion.” Proceedings of Global Power and Propulsion Society. GPPS-TC-2022-0024. 2022.
Pan, T., Yan, Z., Lu, H. and Li, Q. “Numerical Investigation on the Forced Vibration Induced by the Low Engine Order Under Boundary Layer Ingestion Condition.” Aerospace Science and Technology Vol. 115 No. 106802 (2021): p. 10.
Pan, T., Yan, Z., Lu, H., Li, Q. and Kielb, R.E. “Forced Response Induced by Low Engine Order Under Circumferential Inlet Distortions With Different Extents.” Journal of Turbomachinery Vol. 145 No. 4 (2022): p. 12.
Datko, Jr. J.T. and O’Hara, J.A. “The Aeromechanical Response of an Advanced Transonic Compressor to Inlet Distortion.” ASME Turbo Expo: Power for Land, Sea and Air. 79238. 1987.
Zhang, Z., Hou, A., Tuo, W., Xia, A. and Zhou, S. “Forced Response Analysis of Compressor Blades under Unsteady Inlet Distortion.” 31st AIAA Applied Aerodynamics Conference. 2013.
Bréard, C., Vahdati, M., Sayma, A.I. and Imregun, M. “An Integrated Time-Domain Aeroelasticity Model for the Prediction of Fan Forced Response Due to Inlet Distortion.” Journal of Engineering for Gas Turbine and Power Vol. 124 No. 1 (2002): pp. 196–208.
Eichner, F. and Belz, J. “Application of the Modal Approach for Prediction of Forced Response Amplitudes for Fan Blades.” Journal of Engineering for Gas Turbine and Power Vol. 141 No. 3 (2018): p. 8.
Eichner, F., Belz, J., Winkelmann, P., Schnell, R. and Lengyel-Kampmann, T. “Prediction of Aerodynamically Induced Fan Blade Vibration Due to Boundary Layer Ingestion.” 13th European Conference on Turbomachinery Fluid Dynamics Thermodynamics ETC13. 2019.
ANSI and ASME. ANSI/ASME PTC 19.1-2005 Measurement Uncertainty. American Society of Mechanical Engineers (2006).
Dell’Era, G., Habotte, N., Desset, J., Brouckaert, J.F. and Hiernaux, S. “Experimental Characterization of Stall Phenomena in a Single-Stage Low-Pressure Axial Compressor.” Journal of Power and Energy Vol. 229 No. 5 (2015): pp. 549–559.
Toracchio, R., Fontaneto, F. and Hillewaert, K. “On the Impact of the Turbulence Model on the Secondary Flow Structure of a Highly-Loaded Compressor Stage.” Proceedings of ASME Turbo Expo. GT2022-83163. 2022.
Fine/Turbo Theory Guide. Numeca International, 13.2ed (2019).