0
Research Papers

Bleed-Induced Distortion in Axial Compressors

[+] Author and Article Information
S. D. Grimshaw

Whittle Laboratory,
University of Cambridge,
1 JJ Thomson Avenue,
Cambridge CB3 0DY, UK
e-mail: sdg33@cam.ac.uk

G. Pullan

Whittle Laboratory,
University of Cambridge,
1 JJ Thomson Avenue,
Cambridge CB3 0DY, UK

T. Walker

Takasago Research and Development Centre,
Mitsubishi Heavy Industries Ltd.,
Takasago 676-8686, Japan

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 10, 2015; final manuscript received June 8, 2015; published online July 14, 2015. Assoc. Editor: Michael Hathaway.

J. Turbomach 137(10), 101009 (Oct 01, 2015) (9 pages) Paper No: TURBO-15-1088; doi: 10.1115/1.4030809 History: Received May 10, 2015; Revised June 08, 2015; Online July 14, 2015

In this paper, the influence of nonuniform bleed extraction on the stability of an axial flow compressor is quantified. Nonuniformity can be caused by several geometric factors (for example, plenum chamber size or number of off-take ducts), and a range of configurations is examined experimentally in a single stage compressor. It is shown that nonuniform bleed leads to a circumferential distribution of flow coefficient and swirl angle at inlet to the downstream stage. The resultant distribution of rotor incidence causes stall to occur at a higher flow coefficient than if the same total bleed rate had been extracted uniformly around the circumference. A connection is made between the analysis of nonuniform bleed extraction and the familiar DCθ criterion used to characterize inlet total pressure distortion. The loss of operating range caused by the nonuniform inlet flow correlates with the peak sector-averaged bleed nonuniformity for all the bleed configurations tested.

Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 8

Spanwise distribution of rotor inlet relative flow angle, near casing, with φstage = 0.38

Grahic Jump Location
Fig. 7

Rig and stage inlet flow coefficient at stall

Grahic Jump Location
Fig. 6

Unsteady casing pressure transducer traces at rotor inlet at stall

Grahic Jump Location
Fig. 5

Spanwise distributions of flow coefficient through the compressor at different bleed rates, with fixed φstage = 0.43

Grahic Jump Location
Fig. 4

Stage inlet total-to-static pressure rise characteristic

Grahic Jump Location
Fig. 3

Rig inlet total-to-static pressure rise characteristic

Grahic Jump Location
Fig. 2

Detail of bleed slot instrumentation

Grahic Jump Location
Fig. 1

Meridional view of test compressor showing measurement planes

Grahic Jump Location
Fig. 9

Stage inlet total-to-static pressure rise characteristics for uniform and sample nonuniform bleed

Grahic Jump Location
Fig. 10

Variation in local passage-averaged flow coefficient against circumferential position, with φstage = 0.38

Grahic Jump Location
Fig. 11

Comparison of bleed distributions measured in slot and derived from traverse data

Grahic Jump Location
Fig. 12

Change in passage-averaged flow angle compared to mean value, with φstage = 0.38

Grahic Jump Location
Fig. 13

Flow schematic (top) and flow coefficient distributions for isolated bleed extraction with no net main annulus flow

Grahic Jump Location
Fig. 14

Flow schematic (top) and flow coefficient distributions for bleed extraction with swirling main annulus flow

Grahic Jump Location
Fig. 15

Flow angle at measurement point closest to casing (97.2% span), with φstage = 0.38

Grahic Jump Location
Fig. 16

Stage inlet flow coefficient at stall

Grahic Jump Location
Fig. 17

Variation in stage inlet flow coefficient at stall with angular separation of off-take ducts (two duct cases)

Grahic Jump Location
Fig. 18

Variation of local bleed rate in slot with circumferential position relative to off-take duct

Grahic Jump Location
Fig. 19

Obtaining the peak sector-averaged bleed nonuniformity

Grahic Jump Location
Fig. 20

Variation of R2 with sector size

Grahic Jump Location
Fig. 21

Change in stage inlet flow coefficient at stall with bleed nonuniformity (evaluated using a 90 deg sector average)

Tables

Errata

Discussions

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.

Related Journal Articles
Related eBook Content
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