REDUCED DIAMETER CENTRIFUGAL IMPELLER DIFFUSER INVESTIGATION

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$60,951.00
Award Year:
1987
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
5670
Agency Tracking Number:
5670
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
Po Box 643 - Main St, Norwich, VT, 05055
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
DR DAVID JAPIKSE
(802) 649-8875
Business Contact:
() -
Research Institution:
n/a
Abstract
THIS INVESTIGATION EVALUATES A MULTI-ROW STRAIGHT CHANNEL DIFFUSER, A MULTI-ROW CASCADE (AIRFOIL) DIFFUSER, AND A MULTI-ROW DIFFUSER WITH A BEND TO AXIAL, IN ORDER TO CHOOSE THE BEST COMPONENTS NEEDED TO MEET AIRCRAFT RESTRICTED DIAMETER DESIGN REQUIREMENTS. THE SYSTEMATIC DESIGN, FABRICATION AND TEST INCLUDES COMPARISON TO BACKGROUND DATA SETS, AND DETAILED TRAVERSE AND LASER MEASUREMENTS AS WARRENTED. IT IS EXPECTED THAT A DEFINITIVE PREFERENCE FOR THE CHANNEL OR CASCADE DIFFUSER WILL RESULT, THAT BASIC DATA ON RATE OF DIFFUSION WILL BE OBTAINED, THAT ENHANCEMENTS ON THE BEND TO AIXAL WILL BE INTRODUCED IN THE FORM OF FLOW CONTROL, AND THAT THESE TESTS WILL PAVE THE WAY TOWARDS DEFINING OPTIMUM AIRCRAFT ENGINE COMPACT DIFFUSER SYSTEMS. TESTING WILL BE CONDUCTED IN A WELL CALIBRATED, SMALL-SCALE COMPRESSORSTAGE WITH INLET MACH NUMBERS OF ABOUT 1.1.

* information listed above is at the time of submission.

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