Accession Number : ADA295339

Title :   An Analysis of Wake-Stator Interaction in Airfoil Cascades.

Descriptive Note : Final rept. 15 Dec 91-14 Jan 95,

Corporate Author : UNITED TECHNOLOGIES CORP HARTFORD CT

Personal Author(s) : Barnett, M. ; Sondak, D. L.

PDF Url : ADA295339

Report Date : MAR 1995

Pagination or Media Count : 41

Abstract : A computational study has been conducted in order to provide insight into the details of the unsteady flow in the leading-edge region of airfoil cascades during wake-stator interaction. The calculations are performed at off-design operating conditions, since the flow at conditions near to those at which stall onset occurs is of particular interest in helping to understand the mechanisms responsible for compressor stall. A thorough understanding of these mechanisms will provide the underpinnings needed to design compressors with favorable stall characteristics, using fewer design iterations than are typical with the present state of the art. The results obtained during this study show that the use of highly refined grids leads to the resolution of complex unsteady phenomena associated with wake-stator interaction. The structure of the interaction is shown to change significantly as the magnitude of the wake deficit is increased, with shedding from the leading-edge separation bubble suppressed compared to that observed for the cases with small wake deficit or no wake disturbance. (AN)

Descriptors :   *WAKE, *CASCADES(FLUID DYNAMICS), PRESSURE GRADIENTS, MATHEMATICAL MODELS, TIME DEPENDENCE, GRIDS, BOUNDARY LAYER, COMPUTATIONAL FLUID DYNAMICS, VORTEX SHEDDING, AIRFOILS, FLOW FIELDS, STALLING, SHEAR STRESSES, BUBBLES, LEADING EDGES, TWO DIMENSIONAL FLOW, UNSTEADY FLOW, COMPRESSORS, NAVIER STOKES EQUATIONS, FLOW SEPARATION, PRESSURE DISTRIBUTION, GAS SURFACE INTERACTIONS, COMPRESSOR STATORS, ROTOR BLADES(TURBOMACHINERY).

Subject Categories : Fluid Mechanics
      Hydraulic and Pneumatic Equipment

Distribution Statement : APPROVED FOR PUBLIC RELEASE