发明名称 AIRCRAFT GAS TURBINE ENGINE CONTROL
摘要 <p>A normal acceleration schedule limits the rate of engine acceleration. A second acceleration schedule permits a higher acceleration, which causes higher thermal stress in the hot engine parts. The higher schedule is enabled only during a landing approach, thus limiting the number of such stress cycles, while achieving improved performance for the selected mode.</p>
申请公布号 WO1993012331(A1) 申请公布日期 1993.06.24
申请号 US1992008465 申请日期 1992.10.02
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