Accession Number : AD0785276

Title :   Effect of Blade Row Geometry on Axial Flow Rotor Unsteady Response to Inflow Distortions.

Descriptive Note : Technical memo.,

Corporate Author : PENNSYLVANIA STATE UNIV STATE COLLEGE APPLIED RESEARCH LAB

Personal Author(s) : Henderson,Robert E. ; Bruce,Edgar P.

Report Date : 18 JUL 1974

Pagination or Media Count : 34

Abstract : Employing a recently developed experimental apparatus, the authors have measured the unsteady response of an isolated axial flow fan rotor to inflow distortions. The measured quantities include the unsteady normal force and pitching moment on a segment of a single blade operating at various mean angles of attack and the associated distribution of time-mean total pressure change across the rotor. These results are part of a larger program that includes variations in the mean angle of attack in reduced frequency omega, in blade stagger angle, and in blade row space-to-chord ratio (S/C). The effect of variations in omega and S/C on the unsteady response are presented. (Modified author abstract)

Descriptors :   *Turbomachinery, *Axial flow fans, Incompressible flow, Subsonic flow, Cascades(Fluid dynamics), Airfoils, Response

Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE