ADVANCED SECONDARY GAS PATH METHODOLOGY

Award Information
Agency:
Department of Defense
Amount:
$486,233.00
Program:
SBIR
Contract:
N/A
Solitcitation Year:
N/A
Solicitation Number:
N/A
Branch:
Air Force
Award Year:
1992
Phase:
Phase II
Agency Tracking Number:
15022
Solicitation Topic Code:
N/A
Small Business Information
Scientific Research Associates
50 Nye Road Po Box 1058, Glastonbury, CT, 06033
Hubzone Owned:
N
Woman Owned:
N
Socially and Economically Disadvantaged:
N
Duns:
N/A
Principal Investigator
 Dr David V Roscoe
 Principal Investigator
 (203) 659-0333
Business Contact
Phone: () -
Research Institution
N/A
Abstract
AN INNOVATIVE APPROACH IS PROPOSED TO DEVELOP AN INLET/FAN COMPRESSION SYSTEM DESIGN METHODOLOGY FOR THOSE COMPONENTS FOR WHICH THE INLET AND FAN HAVE A STRONG MUTUAL INTERDEPENDENCE AND CANNOT BE CONSIDERED SEPARATELY. THE PROPOSED PHASE I/PHASE II EFFORT WOULD BE PERFORMED WITH SRA AS THE PRIME CONTRACTOR AND TELEDYNE CAE AS A SUBCONTRACTOR. UNDER THIS PROGRAM AN EXISTING STATE-OF-THE-ART NAVIER-STOKES CODE WOULD BE EXTENDED VIA INCORPORATION OF AN ACTUATOR MODEL TO REPRESENT FAN BLADE FORCES. SOLUTION OF THE NAVIER-STOKES EQUATIONS FOR THE DUCT FLOW WITH THE ACTUATOR DISK MODEL WOULD PROVIDE A SOLUTION FOR THE DUCT FLOW INCLUDING THE EFFECT OF FAN BLADE FORCES AND INLET FLOW CONTROL VIA WALL TRANSPIRATION AND SUCTION, UNDER PHASE I A GEOMETRY WOULD BE CHOSEN, THE ACTUATOR DISK MODEL WOULD BE INCORPORATED INTO THE EXISTING CODE, A DEMONSTRATION CALCULATION RUN AND AN ASSESSMENT WOULD BE MADE. PHASE II WOULD INCORPORATE WALL TRANSPIRATION AND SUCTION, GENERALIZE THE ACTUATOR DISK MODEL, POSSIBLY EXTEND THE COMPUTATIONAL PROCEDURE UPSTREAM OF THE INLET ENTRANCE PLANE AND PROVIDE A USER ORIENTED WORKSTATION INTERFACE. IN ADDITION, THE PROCEDURE WOULD BE USED IN THE DESIGN OF AN INLET FAN SYSTEM! FAR THE NEXT GENERATION CRUISE MISSILE AND THE DESIGN WOULD BE BUILT AND TESTED.

* information listed above is at the time of submission.

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