Distributed control system for turbine engines

Journal Article · Fri Jan 01 04:00:00 EST 1999 · Journal of Engineering for Gas Turbines and Power

DOI:https://doi.org/10.1115/1.2816295· OSTI ID:328340

Shaffer, P L ^[1]

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1. General Electric Aircraft Engines, Cincinnati, OH (United States)

A distributed control system (DCS) for a turbine engine has been demonstrated and tested, consisting of prototype electronic interface units (EIUs) connected to data and power busses. In the DCS, a central control computer communicated with smart sensors and smart actuators via a 2.5 megabit/sec digital data bus, using the Fieldbus protocol. Power was distributed to the smart devices as 100 kHz 100V peak AC, allowing light, simple power converters at each smart device. All smart sensors, smart actuators, and cables were dual redundant. The smart actuators received position demand from the central control computer, exchanged data between channels to provide local redundancy management, closed the position loop locally, and reported actuator position to the central controller. Smart sensors converted sensed signals to digital values in engineering units, and performed local built-in tests. Testing of the DCS was done in a closed-loop simulation with an engine model. Frequency response of the DCS was almost identical with the conventional system.

• Sponsoring Organization: USDOE
• OSTI ID: 328340
• Report Number(s): CONF-980615--
• Journal Information: Journal of Engineering for Gas Turbines and Power, Journal Name: Journal of Engineering for Gas Turbines and Power Journal Issue: 1 Vol. 121; ISSN JETPEZ; ISSN 0742-4795
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
ACTUATORS
CABLES
COMPUTERIZED CONTROL SYSTEMS
DATA TRANSMISSION
GAS TURBINE ENGINES
MONITORS
PERFORMANCE