Abstract
When an aircraft is hovering or doing a dive-hike flight at a fixed speed, a constant additional inertial force will be induced to the rotor system of the aero-engine, which can be called a constant maneuver load. Take hovering as an example. A Jeffcott rotor system with a biased rotor and several nonlinear elastic supports is modeled, and the vibration characteristics of the rotor system under a constant maneuver load are analytically studied. By using the multiple-scale method, the differential equations of the system are solved, and the bifurcation equations are obtained. Then, the bifurcations of the system are analyzed by using the singularity theory for the two variables. In the EG-plane, where E refers to the eccentricity of the rotor and G represents the constant maneuver load, two hysteresis point sets and one double limit point set are obtained. The bifurcation diagrams are also plotted. It is indicated that the resonance regions of the two variables will shift to the right when the aircraft is maneuvering. Furthermore, the movement along the horizontal direction is faster than that along the vertical direction. Thus, the different overlapping modes of the two resonance regions will bring about different bifurcation modes due to the nonlinear coupling effects. This result lays a theoretical foundation for controlling the stability of the aero-engine’s rotor system under a maneuver load.
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References
Zhu, C. S. and Chen, Y. J. Vibration characteristics of aero-engine’s rotor system during maneuvering flight. Acta Aeronau Tica et Astronau Tica Sinica, 27(5), 835–841 (2006)
Zhu, C. S. and Chen, Y. J. General dynamic model of aero-engine’s rotor system during maneuvering flight. Journal of Aerospace Power, 24(2), 371–377 (2009)
Wei, H. T. and Fan, X. M. Vibration response analysis of a dual-rotor system during maneuver. 10th Conference of the Structural Strength and Vibration of Aero-Engine, Anhui, 315–320 (2001)
Xu, M. and Liao, M. F. The vibration performance of the Jeffcott rotor system with SFD in maneuver flight. Journal of Aerospace Power, 18(3), 394–401 (2003)
Yang, Y. F., Ren, X. M., and Qin, W. Y. Study of nonlinear response of cracked Jeffcott rotor in hovering state. Journal of Aerospace Power, 22(6), 1007–1012 (2007)
Yang, Y. F., Ren, X. M., and Qin, W. Y. Nonlinear response analysis of a cracked Jeffcott rotor in action of dive-hike. Journal of Vibration and Shock, 26(4), 21–24 (2007)
Yu, Y. B. Research on Aero-Engine Non-linear Characteristics of Cracked Rotor Systems, M. Sc. dissertation, Xi’an Technological University, Xi’an (2009)
Golubistky, M. S. and Schaeffer, D. G. Singularities and Groups in Bifurcation Theory I, SpringVerlag, New York (1985)
Golubistky, M. S. and Schaeffer, D. G. Singularities and Groups in Bifurcation Theory II, SpringVerlag, New York (1988)
Qin, Z. H. and Chen, Y. S. Singular analysis of bifurcation systems with two parameters. Acta Mechanica Sinica, 26(3), 501–507 (2010)
Li, J. and Chen, Y. S. Transition sets of bifurcations of dynamical systems with two state variables with constraints. Applied Mathematics and Mechanics (English Edition), 33(2), 139–154 (2012) DOI 10.1007/s10483-012-1539-7
Zhang, H. B., Chen, Y. S., and Li, J. Bifurcation on the synchronous full annular rub of a rigid-rotor elastic-support system. Applied Mathematics and Mechanics (English Edition), 33(7), 865–880 (2012) DOI 10.1007/s10483-012-1591-7
Hou, L. and Chen, Y. S. Effect of constant maneuver load on vibration characteristics of aeroengine’s rotor system. Journal of Aerospace Power, 28(12), 2790–2796 (2013)
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Project supported by National Basic Research Program (973 Program) of China (No. 2015CB057400)
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Hou, L., Chen, Y. Bifurcation analysis of aero-engine’s rotor system under constant maneuver load. Appl. Math. Mech.-Engl. Ed. 36, 1417–1426 (2015). https://doi.org/10.1007/s10483-015-1992-7
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DOI: https://doi.org/10.1007/s10483-015-1992-7