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Experimental and numerical study of nonlinear interactions in two-dimensional transonic nozzle flow
KTH, Skolan för industriell teknik och management (ITM), Energiteknik, Kraft- och värmeteknologi. L.M.F.A., Ecole CentraleLyonFrance.
KTH, Skolan för industriell teknik och management (ITM), Energiteknik, Kraft- och värmeteknologi.
2006 (Engelska)Ingår i: UNSTEADY AERODYNAMICS, AEROACOUSTICS AND AEROELASTICITY OF TURBOMACHINES / [ed] Hall, KC Kielb, RE Thomas, JP, Ecole Cent Lyon, LMFA, Lyon, France. Royal Inst Technol, Heat & Power Technol, Stockholm, Sweden.: SPRINGER , 2006, s. 463-+Konferensbidrag, Publicerat paper (Refereegranskat)
Abstract [en]

A prerequisite for aeroelastic stability prediction in turbomachines is the understanding of the fluctuating aerodynamic forces acting on the blades. Unsteady transonic flows are complex because of mutual interactions between travelling pressure waves, outlet disturbances, shock motion, and fluctuating turbulent boundary layers. Complex phenomena appear in the shock/boundary layer region and produce phase lags and high time harmonics, which can give a significant contribution to the overall unsteady lift and moment, and therefore affect flatter boundaries, cause large local stresses, or even severely damage the turbo-machine. This paper is concerned with the understanding of phenomena associated with travelling waves in non-uniform transonic flows and how they affect the unsteady pressure distribution on the surface as well as the far field radiated sound. In similitude with turbomachines potential interaction, the emphasis was put on the unsteady interaction of upstream propagating acoustic waves with an oscillating shock in a 2D nozzle flow. Both numerical and experimental studies are carried out and compared with each other. Results showed that the unsteady pressure distribution results from the superposition of upstream and downstream propagating pressure waves, which are partly reflected or absorbed by the oscillating shock. Beside, the phase angle shift underneath the shock location was found to linearly increase with the perturbation frequency, which can be critical regarding aeroelastic stability since it might have a significant impact on the phase angle of the overall aerodynamic force acting on the blade and shift the aerodynamic damping from stable to exciting.

Ort, förlag, år, upplaga, sidor
Ecole Cent Lyon, LMFA, Lyon, France. Royal Inst Technol, Heat & Power Technol, Stockholm, Sweden.: SPRINGER , 2006. s. 463-+
Nyckelord [en]
unsteady fbw, shock motion, shock boundary layer interaction, nozzle fbw
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Identifikatorer
URN: urn:nbn:se:kth:diva-242447DOI: 10.1007/1-4020-4605-7_34ISI: 000237275800034OAI: oai:DiVA.org:kth-242447DiVA, id: diva2:1287401
Konferens
UNSTEADY AERODYNAMICS, AEROACOUSTICS AND AEROELASTICITY OF TURBOMACHINES
Anmärkning

QC 20190211

Tillgänglig från: 2019-02-11 Skapad: 2019-02-11 Senast uppdaterad: 2019-02-11Bibliografiskt granskad

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