ADVANCED SECONDARY GAS PATH METHODOLOGY

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.