Flow through a Compressor Stage

The present effort has led to the development of a numerical procedure of the stage flow field based upon solution of the Navier-Stokes equations. The specific case considered is the basic case in which two-dimensional flow and equal rotor and stator pitch are assumed. The procedure developed is cap...

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Bibliographic Details
Main Authors: Gibeling,H J, Weinberg,B C, Shamroth,S J, McDonald,H
Format: Report
Language:English
Subjects:
AIR FLOW
BLADES
COMPRESSORS
COMPUTERIZED SIMULATION
DOWNSTREAM FLOW
Fluid Mechanics
INTERACTIONS
Jet and Gas Turbine Engines
LEADING EDGES
MATHEMATICAL MODELS
NAVIER STOKES EQUATIONS
NUMERICAL METHODS AND PROCEDURES
PE61102F
PITCH(MOTION)
REGIONS
ROTOR BLADES
STAGING
STATORS
TWO DIMENSIONAL FLOW
WUAFOSR2307A4
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Summary:The present effort has led to the development of a numerical procedure of the stage flow field based upon solution of the Navier-Stokes equations. The specific case considered is the basic case in which two-dimensional flow and equal rotor and stator pitch are assumed. The procedure developed is capable of obtaining periodic solutions for a grid of 7500 points within ten CPU minutes of Cray run time. This represents a very efficient technique which will permit runs of this type on a regular basis, and which will allow extension to either three dimensions or to stages in which rotor and stator have unequal pitch and the multiple stages. The results obtained show the qualitatively expected features. Periodicity was obtained essentially within five cycles. The major effect of the interaction to the specific case considered appeared in the leading edge region of the downstream rotor blade. Significant perturbation pressures were noted, Delta Cp approx. = 0.4, which has major implications regarding unsteady loading and unsteady fluid structure interaction. The concentration of the interaction effect in the leading edge has particular significance in regard to unsteady pitching moment. Although less significant, unsteady effects were noted over the aft portion of the trailing blade, as well as over the entire leading blade.