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TECHNICAL PAPERS

Unsteady Aerodynamics and Aeroacoustics of a High-Bypass Ratio Fan Stage

[+] Author and Article Information
Anil Prasad, Dilip Prasad

Aerodynamics Division, Pratt & Whitney Aircraft Engines, East Hartford, CT 06108

J. Turbomach 127(1), 64-75 (Feb 09, 2005) (12 pages) doi:10.1115/1.1811103 History: Received October 01, 2003; Revised March 01, 2004; Online February 09, 2005
Copyright © 2005 by ASME
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References

Figures

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Real part of unsteady pressure at BPF on a midspan plane through the FEGV
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(a) Magnitude of unsteady pressure at BPF and (b) radial profile of absolute Mach number on a plane downstream of the FEGV
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Meridional view of the flow configuration for coupled simulations of the fan system. The broken lines indicate the locations of the sliding interface planes.
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Comparison of rotor isentropic Mach number distributions at various spanwise locations for a high-power engine setting. Lines: isolated calculation; symbols: coupled calculation (for clarity, only every other point is shown).
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Variation with fan face tip relative Mach number Mf of (a) computed acoustic power level at 1.25 (□) and 2.05 (▵) tip chords upstream of fan tip leading edge, and (b) shock strength Z, and supersonic span fraction σ. The approximate prediction of acoustic power using a one-dimensional analysis is shown in (c).
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Position of the rotor leading-edge shock for several values of fan face tip relative Mach number Mf
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Variation of measured inlet shock noise power level with fan face tip relative Mach number Mf
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Radial profiles at x=2.7 of (a) normalized turbulent kinetic energy and (b) normalized turbulent length scale at the approach (AP), flyover (FY), sideline (SL), and maximum power (MP) conditions
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Streamline patterns near the blade suction surface at the (a) flyover, (b) sideline, and (c) maximum power acoustic conditions. (d) Isentropic Mach number distributions at 80% span for the flyover (- - -), sideline (—) and maximum power (-⋅-⋅-) conditions.
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Flow features associated with the rotor at the approach condition: (a) Streamline pattern near blade suction surface and (b) contours of normalized turbulent kinetic energy at x=2.5
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Average normalized turbulent kinetic energy at x=2.7 as function of fan face tip relative Mach number Mf. The approach (AP), flyover (FY), sideline (SL), and maximum power (MP) conditions are indicated.
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Isentropic Mach number distribution on the IGV at midspan: the time-averaged coupled calculation result (○) is compared with that of the isolated rotor simulation (—).
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Unsteady pressure distribution on the IGV. The real part (upper panel) and imaginary part (lower panel) are shown on the pressure (left) and suction (right) surfaces.
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Normalized turbulent kinetic energy τ associated with the rotor wakes entering the IGV. The IGV leading edges are indicated. The view shown is from downstream and rotor motion is counterclockwise.
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Real part of the rotor-frame unsteady pressure field at the vane passing frequency on (a) a meridional midrotor passage plane and (b) radial plane located at the IGV midspan
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Radial profiles of (a) relative Mach number and (b) relative swirl angle at x=2.5. The splitter location is indicated by the broken line.
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Isentropic Mach number on the FEGV at three spanwise locations obtained from the coupled time-averaged simulation (symbols) and the isolated calculation (lines)
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Comparison of the locus of maximum rotor wake velocity deficit from the coupled (□) and isolated rotor (—) simulations at x=2.75
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Radial profiles at x=2.7 of the (a) magnitude and (b) phase of the normalized gust excitation components at BPF
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Unsteady static pressure perturbation on the FEGV at BPF. The real part (upper panel) and imaginary part (lower panel) are shown on the pressure (left) and suction (right) surfaces.

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