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Distributed Control System for Turbine Engines FREE

[+] Author Affiliations
Phillip L. Shaffer

General Electric Aircraft Engines, Cincinnati, OH

Paper No. 98-GT-016, pp. V005T15A002; 8 pages
doi:10.1115/98-GT-016
From:
  • ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education
  • Stockholm, Sweden, June 2–5, 1998
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7866-8
  • Copyright © 1998 by ASME

abstract

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.

Copyright © 1998 by ASME
This article is only available in the PDF format.

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