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Research Papers

Observer Design for Axial Flow Compressor

[+] Author and Article Information
Xuejun Gao

Faculty of Applied Mathematics,
Guangdong University of Technology,
Guangzhou 510006, China
e-mail: gaoxxj@163.com

Tingwen Huang

Department of Mathematics,
Texas A&M University at Qatar,
Doha 23874, Qatar
e-mail: tingwen.huang@qatar.tamu.edu

Yu Huang

Department of Mathematics,
Zhongshan (Sun Yat-Sen) University,
Guangzhou 510275, China
e-mail: stshyu@mail.sysu.edu.cn

Jun Liu

Department of Mathematics,
Southern Illinois University,
Carbondale, IL 62901
e-mail: junliu2010@siu.edu

MingQing Xiao

Department of Mathematics,
Southern Illinois University,
Carbondale, IL 62901
e-mail: mxiao@siu.edu

1Corresponding author.

Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received November 4, 2012; final manuscript received April 23, 2014; published online July 9, 2014. Assoc. Editor: Nariman Sepehri.

J. Dyn. Sys., Meas., Control 136(5), 051017 (Jul 09, 2014) (12 pages) Paper No: DS-12-1360; doi: 10.1115/1.4027525 History: Received November 04, 2012; Revised April 23, 2014

Flow disturbance is the main cause which leads to the instability occurred in aero-engines, and it is an infinite-dimensional quantity that is impossible for a direct online measurement in reality. The unstable flow not only results in a drastic pressure reduction but also can damage to engine's components during the compressor operations. In this paper, we construct a local state observer which can deliver the full information of the flow disturbance by only sensing on an arbitrarily small area at the duct entrance in terms of averaging the flow disturbance, which provides a practical approach for real applications. The proposed observer makes possible in applications by using a feedback control to stabilize the system. The convergent gain is obtained through the approach of operator spectrum theory. Numerical simulations are provided to illustrate the effectiveness of the proposed observer by showing typical types of flow situations for aero-engine compressors.

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References

Figures

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Fig. 1

An outline of a compression system

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Fig. 2

Compressor geometry

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Fig. 3

Notation used in definition of compressor characteristic with w = 0.5 and H = ψc0 = 2

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Fig. 7

The dynamics of the flow coefficient and the pressure rise coefficient for B = 2 and μ = 0.6 (surge case)

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Fig. 4

The dynamics of the flow coefficient and the pressure rise coefficient for B = 0.5 and μ = 0.565 (rotating stall case)

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Fig. 5

System states (solid line) and estimations (dotted line) for B = 0.5 and μ = 0.565

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Fig. 6

Error dynamics (log ei) for B = 0.5 and μ = 0.565

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Fig. 8

System states (solid line) and estimations (dotted line) for B = 2 and μ = 0.6

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Fig. 9

Error dynamics (log ei) for B = 2 and μ = 0.6

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Fig. 10

The dynamics of the flow coefficient and the pressure rise coefficient for B = 0.72058 and μ = 0.572 (combination of rotating stall and surge)

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Fig. 11

System states (solid line) and estimations (dotted line) for B = 0.72058 and μ = 0.572

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Fig. 12

Error dynamics (log ei) for B = 0.72058 and μ = 0.572

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