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Three-dimensional aerodynamics of an annular airfoil cascade including loading effects

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Abstract

A series of experiments are described which investigate and quantify the effect of loading on the three-dimensional flow through a subsonic annular cascade of cambered airfoils. At two levels of loading, detailed data quantify the cascade inlet velocity, the intrapassage flow field, the airfoil surface pressure distributions, the exit flow field, and the total pressure loss distributions. Aerodynamic loading is shown to strengthen the radial pressure gradient, the passage vortex structure, the vortex-endwall boundary layer interactions, and the losses.

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Abbreviations

C p :

airfoil surface pressure coefficient

C p, loss :

total pressure loss coefficient

U A :

axial velocity component

U n :

velocity in n direction

U r :

velocity in r direction

U R :

radial velocity component

U T :

tangential velocity component

U 0 :

mass averaged inlet velocity

(m, n, r):

local coordinate system

α i :

beam bisector angle to the radial direction

β :

coordinate system rotation

Z c :

chordwise distance from airfoil trailing edge

References

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Authors and Affiliations

  1. Thermal Sciences and Propulsion Center, School of Mechanical Engineering, Purdue University, 47907, West Lafayette, IN, USA

    S. Fleeter, R. C. Stauter & S. R. Manwaring

Authors
  1. S. Fleeter
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  2. R. C. Stauter
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  3. S. R. Manwaring
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Fleeter, S., Stauter, R.C. & Manwaring, S.R. Three-dimensional aerodynamics of an annular airfoil cascade including loading effects. Experiments in Fluids 8, 49–58 (1989). https://doi.org/10.1007/BF00203065

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  • DOI: https://doi.org/10.1007/BF00203065

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