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Boundary Layer Correction of Viscous Flow Through 2 D Turbine Cascades
P M V SubbaraoProfessor
Mechanical Engineering Department
A Classical Method Recommended by Schlichting .……
Validity of Inviscid Flow Theory
Cascade Boundary Layer
Losses in 2D Cascades
• For flow of viscous fluids through two-dimensional cascades, the main object of the investigations has been to find a way to calculate theoretically the loss coefficients of the cascade.
• They depend on the geometrical and aerodynamic parameters of the cascade.
• A turbulent boundary layer computation has been incorporated into the inviscid design.
• This method solves three ordinary differential equations for three independent parameters, the momentum thickness, the shape factor and the entrainment coefficient.
The Displacement Thickness• Conservation of mass is applied to this Engineering CV
@SSSF:0.
CS
Adv
000
H
e
Y
Udyudy
Y
e
dyU
u
0
* 1
Momentum Thickness of BL
Conservation of Integral x momentum
CS
x AdvuDF
.
H
e
Y
UdyUudyuD00
Y
e dyuHUD0
22 Y
e dyuUuUuHUD0
22
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dyU
u
U
u
U
D
02
1
sUsD e 2
Physical Interpretation of Momentum and displacement thicknesses
Their ratio of displacement thickness to momentum thickness is called the shape factor, is often used in estimation of boundary-layer impact on cascade peformance
*
H
U
u
e
1
U
u
U
u
ee
1
BL Correction Equations
dS
dU
UMH
C
ds
d f 222
dS
dU
UH
CHC
dH
Hd
ds
Hd fE
121
1
2
1
2/12/1
1
18.2
MfdS
dU
UdS
dU
UdH
HdCC
HHF
ds
dC
EQEQ
E
Y
e
dyU
uH
0
11
Y
eE udy
ds
d
UC
0
1
Y
e
dyU
uH
0
1
2
2
UC
e
wf
Comparison of optimum solidities
Non-Dimensional Variables for Cascade Analysis
• Non dimensional deflection:f
ru
V
V
• Loss Coefficient: 2
21
fV
h
• Solidity ratio:c
s
• Reynolds Number:
cVr 2Re
Non-Dimensional Variables for Cascades : Design
• Pressure Coefficient:2
21 U
p
• Flow Coefficient:22fVR
Q
f
ru
V
V
f
ru
V
V
Wind Tunnel Testing of Cascades
COMPRESSIBLE CASCADE FLOW
• This is regarded as very important for basic research on cascades, because the aerodynamic coefficients in most cases depend considerably on both the Mach number and the Reynolds number of the blade.
• The independent variation of Mach number and Reynolds number is achieved by installing the cascade wind tunnel in a tank which can be evacuated from 1 atm down to 0.1 atm.
• The Mach number range is from M = 0.2 to about 1.1.
• The blade length L = 300 mm and the blade chord c = 60 mm.
• For one year an extensive programme of pressure distribution measurements has been carried out on cascade blades at high subsonic speeds.
High Speed Wind Tunnel Testing of Cascades
Effect of Mach Number
Effect of Mach Number
Effect of Mach Number