Present turbojet engine control systems, which are comprised of: controller, fuel metering device, sensors, connectors, and harnesses are the single most expensive subsystem on expendable turbojet engines. The size and cost of expendable turbojet engines has steadily decreased. However the engine control system cost has remained relatively constant. Electronic concepts proposes to demonstrate that significant cost reductions can be realized in expendable turbojet engine control systems by: (1) applying highly integrated circuit technology, (2) utilizing a derivative of automotive fuel metering technology, and (3) by integrating the control electronics, engine sensors and fuel metering devices into a single enclosure thus eliminating expensive harnesses and electrical connectors. The Phase I project succeeded in producing a heavy walled prototype of a working control system. The prototype system successfully controlled an expendable turbojet engine during starting, acceleration, and steady state governing. The successful Phase I control system provides the baseline for the Phase II flight weight control system development. Successful completion of the Phase II effort will lay the foundation for the commercialization of an Ultra Low Cost Engine Control System. Anticipated
Benefits: An Ultra Low Cost Engine Control System and associated technology can be directly applied to Commercial and Military turbine engine powered ground start carts, power generating units, and air conditioning carts. In addition a majority of aircraft Auxiliary Power Units (APU's) are powered by small turbine engines which represent an ideal application for Ultra Low Cost Engine Control Systems.
Keywords: DIGITAL ENGINE CONTROL ENGINE CONTROL TURBO ENGINE CONTROL
