Lightweight, Opto-Electronic Engine Control System for Aerospace Turbine Engines
Date Published: 1993-04-01
Paper Number:931442
DOI: 10.4271/931442
Citation:
McRoberts, B. and Walejewski, C., "Lightweight, Opto-Electronic Engine Control System for Aerospace Turbine Engines," SAE Technical Paper 931442, 1993, doi:10.4271/931442.
Author(s):
Bradley J. McRoberts - AlliedSignal Controls & Accessories
Charles T. Walejewski - AlliedSignal Controls & Accessories
AlliedSignal Controls and Accessories (ASCA) in cooperation with Pratt & Whitney Government Engine and Space Propulsion (PW GESP) have demonstrated a lightweight opto-electronic engine control system that features a lightweight fuel throttling valve, lightweight inlet guide vane servoactuator, and an opto-electronic controller with lightweight enclosure. The engine control system was built and tested in support of the first phase of the government sponsored Integrated High Performance Turbine Engine Technology (IHPTET) Initiative.
Both the fuel throttling valve and inlet guide vane servoactuator utilize fiber-optic position feedback sensors, low power, high force lightweight piezoelectric actuated direct drive servovalves, and advanced lightweight materials such as AA-8090 aluminum-lithium, silicon nitride ceramic, carbon fiber composite, and AA-8009 high temperature aluminum. Using these advanced lightweight materials, and employing innovative control techniques and advanced electromechanical interface devices, an overall weight savings of 25% was achieved over baseline YF119 components.
The engine control system has completed over 100 hours of testing on the USAF’s JTDE XTE 65-1B engine with additional testing scheduled for the latter part of 1993. In addition, the components have amassed a total of 50 hours of component acceptance and design verification testing in the laboratory.
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