| タイトル | Digital implementation of the TF30-P-3 turbofan engine control |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750010167 |
| 著者（英） | Batterton, P. G.; Cwynar, D. S. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1975-02-01 |
| 言語 | eng |
| 内容記述 | The standard hydromechanical control modes for TF30-P-3 engine were implemented on a digital process control computer. Programming methods are described, and a method is presented to solve stability problems associated with fast response dynamic loops contained within the exhaust nozzle control. A modification of the exhaust nozzle control to provide for either velocity or position servoactuation systems is discussed. Transient response of the digital control was evaluated by tests on a real time hybrid simulation of the TF30-P-3 engine. It is shown that the deadtime produced by the calculation time delay between sampling and final output is more significant to transient response than the effects associated with sampling rate alone. For the main fuel control, extended update and calculation times resulted in a lengthened transient response to throttle bursts from idle to intermediate with an increase in high pressure compressor stall margin. Extremely long update intervals of 250 msec could be achieved without instability. Update extension for the exhaust nozzle control resulted in a delayed response of the afterburner light-off detector and exhaust nozzle overshoot with resulting fan oversuppression. Long update times of 150 msec caused failure of the control due to a false indication by the blowout detector. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 75N18239
E-8064
NASA-TM-X-3105 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/190905 |
