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
Your Session has timed out. Please sign back in to continue.



Grahic Jump Location
Figure 2

Pressure-rise characteristic of the compressor

Grahic Jump Location
Figure 3

Stalling pattern of the compressor

Grahic Jump Location
Figure 4

Circumferential sensor locations and blade identification

Grahic Jump Location
Figure 5

Pressure field measurement

Grahic Jump Location
Figure 6

Pressure contours (experimental results)

Grahic Jump Location
Figure 7

Signal-processing technique

Grahic Jump Location
Figure 8

Time history of pressure signal at axial locations

Grahic Jump Location
Figure 9

Indication development in axial direction

Grahic Jump Location
Figure 10

Indication development in circumferential direction in uniform inlet flow

Grahic Jump Location
Figure 11

Indication development on rotor blades

Grahic Jump Location
Figure 12

Averaged tip-clearance gap

Grahic Jump Location
Figure 13

Steady-state experiments with airflow rates

Grahic Jump Location
Figure 14

Indication development during inlet distortion

Grahic Jump Location
Figure 15

Flow-field measurement during inlet distortion

Grahic Jump Location
Figure 16

Rotor incidence and indication development during inlet distortion




Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In