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Control system requirements are flowed from three basic sources: 1. Requirements from the engine specification that require no decomposition and flow down directly to components. These consist mainly of "generic" requirements directed at the construction of the components such as structural margins, operational envelope (altitude/Mach number envelope of operation), and maintenance/support guidelines. Requirements of this type are applied to the various components by merely assessing their applicability based on the nature of the component. For example, certain EMI requirements imposed on the engine would be applied to components to which an electrical harness connects, but would not apply to non-electrical components such as plumbing tubes and brackets. This flowdown process is represented by the symbol 2. Requirements that must be derived from the engine specification. These consist mainly of functional requirements originating in the engine specification that are decomposed to the major "module" level. A good example ofthis is thrust range, in which all major engine modules play a part. At the propulsion system level, thrust range is normally specified as a maximum allowable thrust at the idle throttle setting (in order to provide controllable aircraft operation during taxi and maximize aircraft landing gear brake life) and a minimum thrust at intermediate/maximum throttle setting to provide the required aircraft performance specified by the aircraft manufacturer. They also include "generic" requirements that apply to all components but vary in requirement level or value depending on specific component attributes. For example, the thermal environment for each component will depend primarily on the component's axial location within the nacelle and on the presence of heat sources other than the engine case such as bleed air ducts. This flowdown process is represented by the symbol Q 69PDF Image | Improving Gas Turbine Engine Control System
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