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piston size (or pump pressure) covers load uncertainty. However, having an EHSV that is potentially larger than the production version induces some additional risk to the development program since failure mode testing (simulating loss of effector control) would be affected by a faster actuator rate during the simulated failure. This could result in more severe consequences to the engine, such as a higher fan overspeed in the event ofthe nozzle failing in the opening direction due to reduced backpressure in the gas path. This situation could be mitigated by providing the capability to easily change the maximum slew rate through the limiting of EHSV electrical signal current by software or through replaceable hardware stops for the EHSV secondary spool valve. Implementing software limiting would result in a small NRE cost to provide the capability, but would be much easier and quicker to modify during the course ofthe development program (it could potentially be changed during an engine run without even shutting the engine down). In any case, the delivered GTA capability for each function requires careful consideration to determine if excess capability does or does not induce risk into the engine development program. For those situations where excess capability drives additional risk, the capability to "throttle back" to lower levels of capability should be provided by a method that is easily and quickly changed on the engine test stand. 5.2.4 Technology Maturity Considerations Another important consideration for components that would appear to benefit from the GTA development concept is the assessment of technology maturity. Delaying the detailed design of a component with immature technology would be extremely risky without a substantial laboratory/bench development program to mature the technology (reference section 2.1). The interactions between the component and the jet engine environment can be extremely complex, therefore the TRL as defined by the NASA/PW definition should be a 7 or higher, indicating that 101PDF Image | Improving Gas Turbine Engine Control System
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