Titlebook: Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines; Kenneth C. Hall,Robert E. Kielb,Jeffrey P. Thomas Conference pro

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EXPERIMENTAL REDUCTION OF TRANSONIC FAN FORCED RESPONSE BY IGV FLOW CONTROLnic resonance crossings. Sensitivity of resonant response amplitude to full-span TEB flowrate, as well as optimal TEB flowrates, are documented for multiple modes. Resonant response sensitivity was generally characterized by a robust region of substantial attenuation, such that less-than-optimal TEB

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FLUTTER DESIGN OF LOWPRESSURE TURBINE BLADES WITH CYCLIC SYMMETRIC MODES very quick and easy to use. Theory and example applications are presented and compared with the results of full three-dimensional viscous CFD analyses. Reasonable agreement is found. The interaction effects of the cosine and sine modes and the work associated with the steady pressure are shown to generally be significant.

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EXPERIMENTAL AND NUMERICAL INVESTIGATION OF 2D PALISADE FLUTTER FOR THE HARMONIC OSCILLATIONSculations were carried out for the torsional and bending oscillations of the compressor cascade. The comparison of the calculated and experimental results for different conditions of the cascade oscillations has shown the good quantitative and qualitative agreement.

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AXIAL TURBINE BLADE VIBRATIONS INDUCED BY THE STATOR FLOW transformed flow solution is transferred to the finite element model where the blade excitation is obtained. Two reduced geometrical rotor-stator configurations are investigated and compared with respect to the flow field and the resulting blade excitation.

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MISTUNING AND COUPLING EFFECTS IN TURBOMACHINERY BLADINGSy of the present method to accurately capture the dominant effects that influence the aeroelastic behavior of the cascades. Further case studies are performed to assess the influence of alternating and random mistuning on the resonant response amplitudes and on the aeroelastic stability.

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THE EFFECT OF MACH NUMBER ON LP TURBINEWAKE-BLADE INTERACTION reference to a profile designed using current low pressure turbine design practice. Wake traverses using pneumatic probes reveal that the unsteadiness reduced the profile losses up to Mach numbers of 0.9

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Conference proceedings 2006f the art research in the areas of aeroacoustics, aerothermodynamics, computational methods, experimental testing related to flow instabilities, flutter, forced response, multistage, and rotor-stator effects for turbomachinery..

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