This paper describes the modifications made to a successful attached flow transition model to produce a model capable of predicting both attached and separated flow transition. This transition model is used in combination with the Fluent CFD software, which is used to compute the flow around the blade assuming that it remains entirely laminar. The transition model then determines the start of transition location and the development of the intermittency. These intermittency values weight the laminar and turbulent boundary layer profiles to obtain the resulting transitional boundary layer parameters. The ERCOFTAC T3L test cases are used to validate the predictions. The T3L blade is a flat plate with a semi-circular leading edge, which results in the formation of a separation bubble the length of which is strongly dependent on the transition process. Predictions were performed for five T3L test cases for differing free-stream turbulence levels and Reynolds numbers. For the majority of these test cases the measurements were accurately predicted.

1.
Schulte
,
V.
and
Hodson
,
H. P.
, 1998, “
Unsteady Wake-Induced Boundary Layer Transition in High Lift LP Turbines
,”
ASME J. Turbomach.
0889-504X,
120
, pp.
28
35
.
2.
Roberts
,
B.
, 1975, “
The Effect of Reynolds Number and Laminar Separation on Axial Cascade Performance
,”
ASME J. Eng. Power
0022-0825
97
, pp.
261
274
.
3.
Mayle
,
R. E.
, 1991, “
The Role of Laminar-Turbulent Transition in Gas Turbine Engines
,”
ASME J. Turbomach.
0889-504X
113
, pp.
509
537
.
4.
Hatman
,
A.
, and
Wang
,
T.
, 1999, “
A Prediction Model for Separated Flow Transition
,”
ASME J. Turbomach.
0889-504X
121
, pp.
594
602
.
5.
Johnson
,
M. W.
, and
Ercan
,
A. H.
, 1999, “
A Physical Model for Bypass Transition
,”
Int. J. Heat Fluid Flow
0142-727X
20
, pp.
95
104
.
6.
Abu-Ghannam
,
B. J.
, and
Shaw
,
R.
, 1980, “
Natural Transition of Boundary Layers - The Effects of Turbulence, Pressure Gradient and Flow History
,”
J. Mech. Eng. Sci.
0022-2542
22
, pp.
213
228
.
7.
Johnson
,
M. W.
, 2002, “
Predicting Transition Without Empiricism or DNS
,”
ASME J. Turbomach.
0889-504X
124
, pp.
665
669
.
8.
Johnson
,
M. W.
, 2003, “
A Receptivity Based Transition Model
,”
ASME
, ASME Paper No. 2003-GT-30873.
9.
Fasihfar
,
A.
, and
Johnson
,
M. W.
, 1992, “
An Improved Boundary Layer Transition Correlation
,”
ASME
, ASME Paper No. 92-GT-245.
10.
D’Olivio
,
A.
,
Harkins
,
J. A.
, and
Gostelow
,
J. P.
, 2001, “
Turbulent Spots in Strong Adverse Pressure Gradients, Part 1 - Spot Behaviour
,”
ASME
, ASME Paper No. 2001-GT-0194.
11.
Gostelow
,
J. P.
,
Melwani
,
N.
, and
Walker
,
G. J.
, 1996. “
Effects of Streamwise Pressure Gradient on Turbulent Spot Development
,”
ASME J. Turbomach.
0889-504X
118
, pp.
737
743
.
12.
Ludwieg
,
H.
, and
Tillmann
,
W.
, 1950, “
Investigation of the Wall Shear stress in Turbulent Boundary Layers
,” NACA TN1284.
13.
Göksel
,
O. T.
, 1968, “
Some Effects of Spherical Roughness Upon the Incompressible Flow of a Boundary Layer With Zero Pressure Gradient
,” Ph.D. thesis, University of Liverpool.
14.
Coupland
,
J.
, 1995, “
Transition Modelling for Turbomachinery Flows
,” ERCOFTAC Bulletin No. 24, pp
5
8
.
15.
Vicedo
,
J.
,
Vilmin
,
S.
,
Dawes
,
W. N.
, and
Savill
,
A. M.
, 2003, “
Intermittency Transport Modelling of Separated Flow Transition
,”
ASME
, ASME Paper No. GT-2003-38719.
You do not currently have access to this content.