0
Research Papers

Criteria for Spike Initiated Rotating Stall

[+] Author and Article Information
Huu Duc Vo

Department of Mechanical Engineering,  École Polytechnique de Montréal, 2900 boul. Edouard-Montpetit, 2500 ch. de Polytechnique, Montreal, Quebec, H3T 1J4, Canadahuu-duc.vo@polymtl.ca

Choon S. Tan

Department of Aeronautics and Astronautics,  Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139choon@mit.edu

Edward M. Greitzer

Department of Aeronautics and Astronautics,  Massachusetts Institute of Technology, 77 Massachusetts Avenue, Cambridge, MA 02139greitzer@mit.edu

For large tip clearance sizes, as is the case here, steady oscillations in the tip clearance flow were found to occur near the flow solution limit. The values reported are thus time averaged. Similar oscillations were observed by Mailach et al. (15) and Marz et al. (16)

J. Turbomach 130(1), 011023 (Jan 30, 2008) (9 pages) doi:10.1115/1.2750674 History: Received June 23, 2006; Revised June 30, 2006; Published January 30, 2008

A computational study to define the phenomena that lead to the onset of short length-scale (spike) rotating stall disturbances has been carried out. Based on unsteady simulations, we hypothesize there are two conditions necessary for the formation of spike disturbances, both of which are linked to the tip clearance flow. One is that the interface between the tip clearance and oncoming flows becomes parallel to the leading-edge plane. The second is the initiation of backflow, stemming from the fluid in adjacent passages, at the trailing-edge plane. The two criteria also imply a circumferential length scale for spike disturbances. The hypothesis and scenario developed are consistent with numerical simulations and experimental observations of axial compressor stall inception. A comparison of calculations for multiple blades with those for single passages also allows statements to be made about the utility of single passage computations as a descriptor of compressor stall.

Copyright © 2008 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Sketch of incoming/tip clearance flow interface

Grahic Jump Location
Figure 2

Contours of entropy/unit mass at E3 rotor blade tip at the flow solution limit

Grahic Jump Location
Figure 3

Contours of entropy/unit mass at rotor 35 blade tip at flow solution limit/stall point

Grahic Jump Location
Figure 4

Passage pressure rise and blockage as a function of flow coefficient for E3 rotor B; 1.8% chord tip clearance

Grahic Jump Location
Figure 5

Leading-edge tip clearance flow spillage below blade tip

Grahic Jump Location
Figure 6

Mass flow through tip clearance and mass flow spilled ahead of leading edge below blade tip

Grahic Jump Location
Figure 7

Reversal (“backflow”) of tip clearance fluid below the blade tip

Grahic Jump Location
Figure 8

Spanwise distribution of pitch-averaged mass flow at passage exit plane (1.8% chord tip clearance)

Grahic Jump Location
Figure 9

Relative flow vectors and static pressure contour at rotor tip plane during transient beyond equilibrium solution limit. Figs.  99 correspond to point 6, and Figs.  99 to point 8, of Figs.  468.

Grahic Jump Location
Figure 10

Contribution of tip clearance backflow to overall tip region blockage

Grahic Jump Location
Figure 11

Role of leading-edge spillage on upstream propagation of backflow

Grahic Jump Location
Figure 12

Evaluation of passage flow solution limit criteria for 3.0% chord tip clearance: (a) passage pressure rise and blockages, (b) spanwise distribution of pitch-averaged mass flow at passage exit plane, and (c) mass flow through blade tip and spilled ahead of leading edge below blade tip

Grahic Jump Location
Figure 13

Stall transient for multiple (six) blade passage configuration

Grahic Jump Location
Figure 14

Relative flow vectors at blade tip at time 4 of stall transient in Fig. 1

Grahic Jump Location
Figure 15

Relative flow vectors at blade tip in single blade passage computation at a flow coefficient near that of passage 3 in Fig. 1

Grahic Jump Location
Figure 16

Tip clearance flow behavior in each blade passage at time (4): (a) spanwise distribution of pitch-averaged mass flow at passage exit plane and (b) leading-edge spillage of tip clearance fluid below the blade tip

Tables

Errata

Discussions

Related

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