INVESTIGATION OF WEIS-FOGH PRINCIPLE OF HIGH LIFT AS APPLIEDTO TURBOMACHINERY FLOWS

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$48,807.00
Award Year:
1987
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Agency Tracking Number:
5180
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Vigyan Research Assocs Inc.
30 Research Drive, Hampton, VA, 23666
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
() -
Business Contact:
Dr. P. Sundaram
Research Engineer
() -
Research Institution:
n/a
Abstract
THE PROPOSED RESEARCH IS DIRECTED TOWARDS A DETAILED ANALYTICAL AND NUMERICAL STUDY OF THE UNSTEADY VORTEX MOTIONIN THE CLAP-FLING MOTION, OBSERVED BY WEIS-FOGY, WHICH COULDYIELD LIFT COEFFICIENTS OF UP TO EIGHT. THE APPLICATION OF THE CLAP-FLING MOTION ANALOGY TO A COMPRESSOR STAGE COULD, UNDER CERTAIN CIRCUMSTANCES, PREDICT A STRONG ROTOR-STATOR INTERACTION WHICH COULD YIELD AN IMPROVED STAGE PERFORMANCE.THE ANALYTICAL STUDY AND THE NUMERICAL IMPLEMENTATION OF THEMOTION WILL INVOLVE ANALYSING THE UNSTEADY VORTEX FLOW PATTERN OBTAINED FROM THE SOLUTION OF THE TIME DEPENDENT INCOMPRESSIBLE NAVIER-STOKES EQUATION. THE PROPOSED NUMERICAL METHOD UTILIZES THE ADAPTIVE GRID FORMULATION DEVELOPED FOR MULTIPLE BODIES. THE INCREASE IN EFFICIENCY THAT COULD BE OBTAINED BY USING THIS NUMERICAL METHOD FOR A COMPRESSOR STAGE WILL BE COMPARED TO THAT OF A COMPRESSOR STAGE EMPLOYING THE CLASSICAL KUTTA ROTOR. THE EFFECTIVENESS AND ADVANTAGE OF THIS METHOD FOR DELAYING THE ONSET OF STALL ON TURBOMACHINARY BLADES THAT COULD RESULT IN A SIGNIFICANT PRACTICAL ADVANTAGE OVER CONVENTIONAL MACHINARY DESIGNED ON THE AERODYNAMIC PRINCIPLES OF NON-INTERACTING ROTOR-STATOR CONCEPT WILL BE ESTABLISHED. THE EFFECT OF ADDING THE VISCOSITY ON THE RESULTING VORTEX FLOW PATTERN WILL BE STUDIED.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government