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TECHNICAL PAPERS

Early Stall Warning Technique for Axial-Flow Compressors

[+] Author and Article Information
Nobuyuki Tahara, Takurou Nakajima, Tomofumi Nakakita

 Ishikawajima-Harima Heavy Industries, Toyosu, Tokyo, 135-8710 Japan

Masahiro Kurosaki

 Ishikawa National College of Technology, Kahoku-gun, Ishikawa, 929-0392 Japan

Yutaka Ohta, Eisuke Outa

 Waseda University, Shinjuku, Tokyo, 169-8555 Japan

J. Turbomach 129(3), 448-456 (Jul 29, 2006) (9 pages) doi:10.1115/1.2447948 History: Received July 02, 2006; Revised July 29, 2006

This paper proposes a unique stall risk index based on pressure signals by high-response transducers on the casing wall at the rotor leading-edge location. The aim of the research is to explore the possibility of reducing current excessive stall margin requirement for compressor design based on the worst-case scenario. The index is generated by computing correlation degradation of pressure time histories of current and one revolution before over each blade pitch. Tests conducted on a single-stage low-speed compressor exhibits that the correlation diminishes significantly with proximity to stall, and the proposed technique might have the capability of generating a stall warning signal sufficiently in advance of spike inception. Extensive experiments on a research compressor show that the degree of the index degradation depends on various factors, such as flow coefficient, tip clearance, and rotor blade incidence. In order to obtain a reliable stall warning signal in practical use, these effects must be carefully examined.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

Pressure-rise characteristic of the compressor

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Figure 3

Stalling pattern of the compressor

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Figure 4

Circumferential sensor locations and blade identification

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Figure 5

Pressure field measurement

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Figure 6

Pressure contours (experimental results)

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Figure 7

Signal-processing technique

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Figure 8

Time history of pressure signal at axial locations

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Figure 9

Indication development in axial direction

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Figure 10

Indication development in circumferential direction in uniform inlet flow

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Figure 11

Indication development on rotor blades

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Figure 12

Averaged tip-clearance gap

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Figure 13

Steady-state experiments with airflow rates

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Figure 14

Indication development during inlet distortion

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Figure 15

Flow-field measurement during inlet distortion

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Figure 16

Rotor incidence and indication development during inlet distortion

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