Research Papers

Unsteady Flow and Aeroelasticity Behavior of Aeroengine Core Compressors During Rotating Stall and Surge

[+] Author and Article Information
M. Vahdati, G. Simpson, M. Imregun

Mechanical Engineering Department, Imperial College of Science, Technology and Medicine, London SW7 2BX, UK

J. Turbomach 130(3), 031017 (May 06, 2008) (9 pages) doi:10.1115/1.2777188 History: Received February 20, 2007; Revised February 22, 2007; Published May 06, 2008

This paper will focus on two core-compressor instabilities, namely, rotating stall and surge. Using a 3D viscous time-accurate flow representation, the front bladerows of a core compressor were modeled in a whole-annulus fashion whereas the rest of bladerows were represented in single-passage fashion. The rotating stall behavior at two different compressor operating points was studied by considering two different variable-vane scheduling conditions for which experimental data were available. Using a model with nine whole bladerows, the unsteady flow calculations were conducted on 32 CPUs of a parallel cluster, typical run times being around 3–4 weeks for a grid with about 60×106 points. The simulations were conducted over several engine rotations. As observed on the actual development engine, there was no rotating stall for the first scheduling condition while malscheduling of the stator vanes created a 12-band rotating stall which excited the rotor blade first flap mode. In a separate set of calculations, the surge behavior was modeled using a time-accurate single-passage representation of the core compressor. It was possible to predict not only flow reversal into the low pressure compression domain but also the expected hysteresis pattern of the surge loop in terms of its mass flow versus pressure characteristic.

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



Grahic Jump Location
Figure 4

Hybrid single-passage, whole-annulus model

Grahic Jump Location
Figure 8

Time history of mass flow and blade forcing (upper plot); Fourier components of forcing (lower plot)

Grahic Jump Location
Figure 9

Overall performance: DS versus MS

Grahic Jump Location
Figure 10

Front stage performance

Grahic Jump Location
Figure 11

Total pressure along compressor

Grahic Jump Location
Figure 3

Comparison of computed total pressure (▵) at rotor exit against test data (◻)

Grahic Jump Location
Figure 2

Steady-state flow domain

Grahic Jump Location
Figure 1

Compressor characteristic

Grahic Jump Location
Figure 5

Mistuning pattern to initiate rotating stall

Grahic Jump Location
Figure 6

Time history of negative axial flow at midpassage

Grahic Jump Location
Figure 7

Hysteresis loop for mass flow versus pressure ratio

Grahic Jump Location
Figure 12

Instantaneous static pressure upstream of Rotor 1: DS versus MS

Grahic Jump Location
Figure 13

Static pressure upstream of Rotor 1 and its Fourier components at 70% and 90% height

Grahic Jump Location
Figure 14

Development of stall cell

Grahic Jump Location
Figure 15

Instantaneous negative axial velocity at 70% height

Grahic Jump Location
Figure 16

Fourier components of axial velocity upstream of rotor blades

Grahic Jump Location
Figure 17

Fourier components of forcing on the blade



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