Transition onset observations from a 1.5-stage axial compressor outlet stator presented in Part I of this paper are compared with the predictions of conventional transition correlations applied in a quasi-steady manner. The viscous/inviscid interaction code MISES is used to predict the blade surface pressure distributions and boundary layer development. The temporal variation in transition onset is then predicted using ensemble-averaged free-stream turbulence data from the compressor measurements. This simple procedure captures most significant features of the complex transition process on the compressor, and is clearly superior to fixed transition models based on long-term average free-stream turbulence levels. Parallel computations for both natural and bypass transition modes indicate that the natural transition mode tends to dominate on the compressor. This is at variance with turbine airfoil experience, where bypass transition is clearly more important. Comparison of prediction and experiment highlights the significance of leading edge potential flow interactions in promoting periodic wake-induced transition. Viscous/inviscid interactions in the neighborhood of transition can also have an important influence on boundary layer stability and separation phenomena.

1.
Abu-Ghannam
B. J.
, and
Shaw
R.
,
1980
, “
Natural Transition of Boundary Layers—the Effects of Pressure Gradient and Flow History
,”
Journal of Mechanical Engineering Science
, Vol.
22
, No.
5
, pp.
213
228
.
2.
Addison
J. S.
, and
Hodson
H. P.
,
1990
, “
Unsteady Transition in an Axial Flow Turbine: Part 2—Cascade Measurements and Modeling
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
112
, pp.
215
221
.
3.
Blight, F. G., and Howard, W., 1952, “Tests on Four Aerofoil Cascades. Part 1: Deflection, Drag and Velocity Distribution,” Report E 74, Aeronautical Research Laboratories, Melbourne, Australia.
4.
Chakka
P.
, and
Schobeiri
M. T.
,
1999
, “
Modeling Unsteady Boundary Layer Transition on a Curved Plate Under Periodic Unsteady Flow Conditions: Aerodynamic and Heat Transfer Investigations
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
121
, pp.
88
97
.
5.
Cherret, M. A., 1996, “Rotor–Stator Interactions in a High-Speed Axial Compressor,” pp. 40.1–40.14, Loss Mechanisms and Unsteady Flows in Turbomachines, AGARD CP-571, NATO.
6.
Drela, M., 1995, “MISES Implementation of Modified Abu-Ghannam/Shaw Transition Criterion,” MISES Code Documentation, MIT.
1.
Halstead
D. E.
,
Wisler
D. C.
,
Okiishi
T. H.
,
Walker
G. J.
,
Hodson
H. P.
, and
Shin
H.-W.
,
1997
, “
Boundary Layer Development in Axial Compressors and Turbines: Parts 1–4
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
119
; Part 1: pp.
114
127
;
2.
Part 2
,
ASME JOURNAL OF TURBOMACHINERY
, Vol.
119
, pp.
426
444
;
3.
Part 3
,
ASME JOURNAL OF TURBOMACHINERY
, Vol.
119
, pp.
225
237
;
4.
Part 4
,
ASME JOURNAL OF TURBOMACHINERY
, Vol.
119
, pp.
128
139
.
1.
Hobson, G. V., Wakefield, B. E., and Roberts, W. B., 1996, “Turbulence Amplification With Incidence at the Leading Edge of a Compressor Cascade,” ASME Paper No. 96-GT-409.
2.
Johnson, M. W., and Ercan, A. H., 1996, “A Boundary Layer Transition Model,” ASME Paper No. 96-GT-444.
3.
Mack, L. M., 1977, “Transition and Laminar Instability,” Jet Propulsion Laboratory Publication 77-15, Pasadena, CA.
4.
Mayle
R. E.
,
1991
, “
The Role of Laminar–Turbulent Transition in Gas Turbine Engines
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
113
, pp.
509
537
, The 1991 IGTI Scholar Lecture.
5.
Mayle
R. E.
, and
Schulz
A.
,
1997
, “
The Path to Predicting Bypass Transition
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
119
, pp.
405
411
.
6.
Schulte
V.
, and
Hodson
H. P.
,
1998
, “
Prediction of the Becalmed Region for LP Turbine Profile Design
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
120
, pp.
839
846
.
7.
Solomon, W. J., 1996, “Unsteady boundary Layer Transition on Axial Compressor Blades,” Ph.D. Thesis, University of Tasmania, Hobart.
8.
Solomon, W. J., Walker, G. J., and Gostelow, J. P., 1996, “Transition Zone Predictions for Rapidly Varying Flows,” Henekes, R. A. W. M., and van Ingen, J. L., eds., Transitional Boundary Layers in Aeronautics, North-Holland, pp. 321–332.
9.
Walker, G. J., 1972, “An Investigation of the Boundary Layer Behaviour on the Blading of a Single-Stage Axial-Flow Compressor,” Ph.D. Thesis, University of Tasmania, Australia.
10.
Walker
G. J.
, and
Gostelow
J. P.
,
1990
, “
Effects of Adverse Pressure Gradients on the Nature and Length of Boundary Layer Transition
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
112
, pp.
196
205
.
11.
Walker
G. J.
,
Hughes
J. D.
,
Ko¨hler
I.
, and
Solomon
W. J.
,
1998
, “
The Influence of Wake–Wake Interactions on Loss Fluctuations of a Downstream Axial Compressor Blade Row
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
120
, pp.
695
704
.
12.
Walker, G. J., Hughes, J. D., Solomon, W. J., and Ko¨hler, I., 1997, “Wake Mixing and Blade Clocking Effects in an Axial Compressor,” Proc. 13th Int. Symp. on Air Breathing Engines, Chattanooga.
13.
Youngren, H., and Drela, M., 1991, “Viscous–Inviscid Method for Preliminary Design of Transonic Cascades,” presented at the AIAA Joint Propulsion Conference.
This content is only available via PDF.
You do not currently have access to this content.