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Improving Gas Turbine Engine Control System

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Improving Gas Turbine Engine Control System ( improving-gas-turbine-engine-control-system )

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prognostication of future maintenance needs before they become safety issues. The latter need is only recently becoming feasible with the development of on-board electronics, sensor suites, and software algorithms that can sense and record this data. With this capability, operators can better manage maintenance operations to minimize or prevent disruption of flight operations due to unplanned maintenance activities. The remainder and vast majority ofneeds satisfied by the control system are one or more levels of decomposition deep and as such are derived. The basic architectural concept of the engine must be defined in order to completely define the needs for engine control. Approximately half of the high-level needs for engine control and diagnostics are "generic" in nature (i.e. they are present on nearly every gas turbine engine, regardless of engine architecture) and half are specific to the thrust-producing and airframe installation concepts chosen for the propulsion system. This is discussed in more detail in section 2.2.1. 1.3.2 Concept Generation & Evaluation The current state of technology, corporate strategy, regulations, and customer expectations also play a significant role in concept selection. Propulsion system concepts are selected to meet customer needs based on many criteria, but the significant ones are: * Engine/Aircraft Performance " Current State of Technology Maturity " Historical Success of Similar Products At this step, these criteria are usually applied not only at the highest level of abstraction (i.e. the propulsion system) to define the basic engine parameters such as airflow rating and engine cycle, but also at the first level of decomposition (i.e. at the major engine module level). For example, in the case of the engine control system, an electrical actuation system might be 26

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