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Electronic Control System for a Modern Turboprop Engine
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English
Abstract
The basic objective was to create an integrated fuel control and propeller governor system fully compatible with engine characteristics so that optimum engine performance would be attained during all ground and flight operation within the engine operating envelope.
This system requires less aircraft linkage, a reduction in the number of engine control components, a reduction in the hydromechanical unit complexity, and ease of controls settings adjustment, compared to the current production control systems.
The control system employs electronic, hydraulic, pneumatic, and mechanical components, which result in enhanced performance and reliability characteristics. The system provides automatic starting, engine starting speed switching functions, acceleration fuel scheduling, fuel governor, power settings, engine torque limiting, engine gas temperature limiting, engine gas temperature signal modification to provide “Single Red Line” operation, isochronous propeller governing, overspeed protection, and monitoring functions. The monitors will switch the computer and system to “Manual Mode” when the monitor limits are exceeded, and flight may be continued.
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