A comparison study of turbo-shaft engine fast response control schemes in power recovery process during helicopter autorotation

被引：0
|
作者：
Hua W. [1 ,2 ]
Deng Y. [3 ]
Zhang H.-B. [1 ]
Huang J.-Q. [1 ]
机构：
[1] Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing
[2] China Aviation Industry Corp Aviation Power Control System Research Institute, Wuxi
[3] China Southern Aviation Industry (Group) Co., Ltd, Zhuzhou
来源：
| 1600年 / Journal of Propulsion Technology卷 / 37期
关键词：
Autorotation power recovery; Fast response; Multi-variable control; Turbo-shaft engine;
D O I：
10.13675/j.cnki.tjjs.2016.04.020
中图分类号：
学科分类号：
摘要：
For getting a safer and faster power recovery in helicopter autorotation, two new control schemes for turbo-shaft engines are proposed herein to realize engine output torque fast response and therefor lower rotor speed droop, fully taking advantage of compressor guided vanes or turbine bleeding. On the basis of H2/H∞ performance guaranteed design algorithm, two novel fast response control schemes for turbo-shaft engines are devised, which are fuel flow cooperating with compressor guided vanes control, and fuel flow combined with turbine bleeding control, respectively. These two methods can make the output torque response faster under a safe stall margin and limit the free turbine speed droop less than 3% during power recovery process in helicopter autorotation, otherwise the droop value about 5% when employing the traditional fuel flow control. Moreover, the fuel flow transient using the new methods is smoother than that when using the traditional one. At last, simulation results give comparisons between these two control methods, and the merits as well as its defections are also discussed. © 2016, Journal of Propulsion Technology. All right reserved.
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页码：749 / 757
页数：8
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