Patent ID: 8140242
Filing Date: 2012-03-20
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. A gas turbine engine system comprising: an engine electronic control (EEC) operative to receive and provide information corresponding to engine operating parameters such that a gas turbine engine operates in accordance with the information provided from the EEC; multiple control devices, each of the control devices being operative to perform at least one of: monitoring at least one engine operating parameter, providing information corresponding to the at least one engine operating parameter for use by the EEC, and affecting at least one engine operating parameter; a signal relay device operative to receive multiplexed signals from the EEC, demultiplex the signals, and provide demultiplexed signals to corresponding ones of the multiple control devices wherein said multiplexed/demultiplexed signals are for distribution to non-flight critical control systems only.