| タイトル | Active Control of High Frequency Combustion Instability in Aircraft Gas-Turbine Engines |
| 本文（外部サイト） | http://hdl.handle.net/2060/20030068103 |
| 著者（英） | Corrigan, Bob; Chang, Clarence T.; DeLaat, John C. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2003-09-01 |
| 言語 | eng |
| 内容記述 | Active control of high-frequency (greater than 500 Hz) combustion instability has been demonstrated in the NASA single-nozzle combustor rig at United Technologies Research Center. The combustor rig emulates an actual engine instability and has many of the complexities of a real engine combustor (i.e. actual fuel nozzle and swirler, dilution cooling, etc.) In order to demonstrate control, a high-frequency fuel valve capable of modulating the fuel flow at up to 1kHz was developed. Characterization of the fuel delivery system was accomplished in a custom dynamic flow rig developed for that purpose. Two instability control methods, one model-based and one based on adaptive phase-shifting, were developed and evaluated against reduced order models and a Sectored-1-dimensional model of the combustor rig. Open-loop fuel modulation testing in the rig demonstrated sufficient fuel modulation authority to proceed with closed-loop testing. During closed-loop testing, both control methods were able to identify the instability from the background noise and were shown to reduce the pressure oscillations at the instability frequency by 30%. This is the first known successful demonstration of high-frequency combustion instability suppression in a realistic aero-engine environment. Future plans are to carry these technologies forward to demonstration on an advanced low-emission combustor. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | ISABE-2003-1054
E-14169
NASA/TM-2003-212611
NAS 1.15:212611 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/64032 |
