Gain scheduling control of aero-engine based on mixing polynomial LPV synthesis
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Bin Shen
and
Zhifeng Ye
Abstract
A full envelope LMI-based multi-region linear parameter-varying power controller is designed for a turbofan engine in this paper. According to the characteristics of aero-engine model, three scheduling variables are divided into two groups firstly, and then part of them are partitioned, rather than all scheduling variables are partitioned directly as the usual multi-region LPV control. The polynomial LPV model of aero-engine is established under a specific flight condition. An explicit LPV controller by gridding method based on parameter-dependent Lyapunov function is designed and we propose a method to eliminate the dependence of LPV controller on the derivative of scheduling parameter. The flight envelope of turbofan engine is divided into multiple sub-regions, and a mixing LPV control method with overlapping regions is proposed, which can guarantee stability and performance across the full envelope. Finally, the simulation results on the nonlinear component level model of a twin-spool turbofan engine verify our method.
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work is supported by the National Natural Science Foundation of China (No. 51876089).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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Articles in the same Issue
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- Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor
- Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine
- Probabilistic analysis of maximum mode shape for mistuned blisk
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- A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
- Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
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Articles in the same Issue
- Frontmatter
- Experimental and numerical study of flame structure and emissions in a micro gas turbine combustor
- Influence of innovative hydrogen multi strut injector with different spacing on cavity-based scramjet combustor
- Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine
- Probabilistic analysis of maximum mode shape for mistuned blisk
- Gain scheduling control of aero-engine based on mixing polynomial LPV synthesis
- A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models
- Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade
- Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine
- Supersonic jet mixing in the presence of two annular co-flow streams
- A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption
- Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle
- Numerical investigation of ice crystal melting characteristic and icing risk in an axial compressor
