The two-dimensional steady and unsteady flow field at midspan in a turbine rotor has been investigated experimentally using an LDV with an emphasis on the interaction of the nozzle wake with the rotor flow field. The velocity measurements are decomposed into a time-averaged velocity, a periodic velocity component, and an unresolved velocity component. The results in the rotor passage were presented in Part I. The flow field downstream of the rotor is presented in this paper. The rotor wake profiles and their decay characteristics were analyzed. Correlations are presented that match the decay of the various wake properties. The rotor wake velocity defect decays rapidly in the trailing edge region, becoming less rapid in the near and far wake regions. The rotor wake semi-wake width increases rapidly in the trailing edge region and then grows more gradually in the near and far wake regions. The decay of the maximum unresolved unsteadiness and maximum unresolved velocity cross correlations is very rapid in the trailing edge region and this trend slows in the far wake region. In the trailing edge region, the maximum periodic velocity correlations are much larger than the maximum unresolved velocity correlations. But the periodic velocity correlations decay much faster than the unresolved velocity correlations. The interactions of the nozzle and rotor wakes are also studied. While the interaction of the nozzle wake with the rotor wake does not influence the decay rate of the various wake properties, it does change the magnitude of the properties. These and other results are presented in this paper.

1.
Adamczyk, J. J., 1985, “Model Equations for Simulating Flows in Multistage Turbomachines,” ASME Paper No. 85-GT-226.
2.
Dring. R. P., Joslyn, H. D., and Blair, M. F., 1987, “The Effects of Inlet Turbulence and Rotor/Stator Interactions on the Aerodynamics and Heat Transfer of a Large-Scale Rotating Turbine Model,” NASA-CR-179469, Vol. 4.
3.
Gregory-Smith
D. G.
,
Graves
C. P.
,
Walsh
J. A.
,
1988
, “
Growth of Secondary Losses and Vorticity in an Axial Turbine Cascade
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
110
, pp.
1
8
.
4.
Ho
Y. H.
, and
Lakshminarayana
B.
,
1996
, “
Computational Modeling of Three-Dimensional Flow Through a Turbine Rotor Cascade With Strong Secondary Flows
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
118
, pp.
250
261
.
5.
Hobson, G., and Lakshminarayana, B., 1990, “Computation of Turbine Flow Fields With Navier–Stokes Equations,” AIAA Paper No. 90-2122.
6.
Lakshminarayana
B.
, and
Reynolds
B.
,
1979
, “
Turbulence Characteristics in the Near Wake of a Compressor Rotor Blade
,”
AIAA Journal
, Vol.
18
, No.
11
, pp.
1354
1362
.
7.
Raj
R.
, and
Lakshminarayana
B.
,
1973
, “
Characteristics of the Wake Behind a Cascade of Airfoils
,”
J. Fluid Mech.
, Vol.
61
, part 4, pp.
707
730
.
8.
Raj
R.
, and
Lakshminarayana
B.
,
1976
, “
Three-Dimensional Characteristics of Turbulent Wakes Behind Rotors of Axial Flow Turbomachinery
,”
ASME Journal of Engineering for Power
, Vol.
98
, pp.
218
228
.
9.
Ravindranath, A., 1979, “Three-Dimensional Mean and Turbulence Characteristics of the Near Wake of a Compressor Rotor Blade,” M. S. Thesis, Department of Aerospace Engineering, The Pennsylvania State University.
10.
Ravindranath
A.
, and
Lakshminarayana
B.
,
1980
, “
Mean Velocity and Decay Characteristics of the Near and Far-Wake of a Compressor Rotor Blade of Moderate Loading
,”
ASME Journal of Engineering for Power
, Vol.
102
, pp.
535
548
.
11.
Reynolds, B. D., and Lakshminarayana, B., 1979, “Characteristics of Lightly Loaded Fan Rotor Blade Wakes,” NASA CR-3188.
12.
Reynolds
B.
,
Lakshminarayana
B.
, and
Ravindranath
A.
,
1979
, “
Characteristics of the Near Wake of a Compressor or a Fan Rotor Blade
,”
AIAA Journal
, Vol.
17
, No.
9
, pp.
959
967
.
13.
Schlichting, H., 1979, Boundary Layer Theory, McGraw-Hill, New York.
14.
Sitaram, N., and Govardhan, M., 1986, “Effect of Incidence Angle on Wake Characteristics of High Deflection Turbine Rotor Linear Cascade,” Presented at 9th Australasian Fluid Mechanics Conference, Auckland, Dec.
15.
Spence, D. A., 1953, British Aero. Research Council C. P., No. 125.
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