Transonic Fan/Compressor Rotor Design Study. Volume 2

Parker, D.; Simonson, Margaret

doi:10.21236/adb069402

Cited by 3 publications

(1 citation statement)

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“…19 The stage is composed of 20 low-aspect-ratio rotor blades and 31 stator blades. To model the blockage effects through the stage as accurately as possible, two rotor blade passages and three stator blade passages are modeled along with a time-lagged periodic boundary condition treatment.…”

Section: Resultsmentioning

confidence: 99%

Unsteady Aerodynamic Flow Phenomena in a Transonic Compressor Stage

Hah

Puterbaugh

Copenhaver

1997

Journal of Propulsion and Power

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A three-dimensional unsteady, viscous aerodynamic analysis has been developed for the ow inside a transonic, high-through-ow, single-stage compressor. The compressor stage is comprised of a low-aspectratio rotor and a closely coupled stator. The analysis is based on a numerical method for solving the three-dimensional Navier -Stokes equation for unsteady viscous ow through multiple turbomachinery blade rows. The method solves the fully three-dimensional Navier -Stokes equation with an implicit scheme. A two-equation turbulence model with a low Reynolds number modi cation is applied for the turbulence closure. A third-order accurate upwinding scheme is used to approximate convection terms, whereas a second-order-accurate central difference scheme is used for the discretization of the viscous terms. A second-order accurate scheme is employed for the temporal discretization. The numerical method is applied to study the unsteady ow eld inside a transonic, high-through-ow, axial compressor stage. The numerical results are compared with available experimental data. Nomenclatureconstants in turbulence closure models e = total energy F = body force k = turbulent kinetic energy M = Mach number Pr = Prandtl number p = pressure R = gas constant T = temperature t = time U, V, W = mean velocity components u, v, w = uctuating velocity components dij = Kronecker delta « = turbulence dissipation rate « ijk = permutation symbol m = viscosity n = kinematic viscosity r = density s k , s « = constants in turbulence closure models f = any time-dependent term V = angular velocity Subscript eff = effective value

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Section: Resultsmentioning

confidence: 99%

Unsteady Aerodynamic Flow Phenomena in a Transonic Compressor Stage

Hah

Puterbaugh

Copenhaver

1997

Journal of Propulsion and Power

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Flow Field Unsteadiness in the Tip Region of a Transonic Compressor Rotor

Puterbaugh

Copenhaver

1997

Journal of Fluids Engineering

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An experimental investigation concerning tip flow field unsteadiness was performed for a high-performance, state-of-the-art transonic compressor rotor. Casing-mounted high frequency response pressure transducers were used to indicate both the ensemble averaged and time varying flow structure present in the tip region of the rotor at four different operating points at design speed. The ensemble averaged information revealed the shock structure as it evolved from a dual shock system at open throttle to an attached shock at peak efficiency to a detached orientation at near stall. Steady three-dimensional Navier Stokes analysis reveals the dominant flow structures in the tip region in support of the ensemble averaged measurements. A tip leakage vortex is evident at all operating points as regions of low static pressure and appears in the same location as the vortex found in the numerical solution. An unsteadiness parameter was calculated to quantify the unsteadiness in the tip cascade plane. In general, regions of peak unsteadiness appear near shocks and in the area interpreted as the shock-tip leakage vortex interaction. Local peaks of unsteadiness appear in mid-passage downstream of the shock-vortex interaction. Flow field features not evident in the ensemble averaged data are examined via a Navier-Stokes solution obtained at the near stall operating point.

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