improving durability of turbine components through ...€¦ · bi∞ = h∞ t/k w 0.27 0.30 - 0.77...
TRANSCRIPT
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1
Improving Durability of Turbine Components Through Trenched Film Cooling
and Contoured Endwalls
Principal Investigator:
Prof. David G. Bogard University of Texas at Austin
Co-Principal Investigator:
Prof. Karen A. Thole Pennsylvania State University
Graduate Research Assistant: Amy Mensch
Background image: [Hamed, A., Tabakoff, W., and Wenglarz, R., 2006]
DOE Award Number DE-FE0005540 UTSR Project Number 07-01-SR127
UTSR Workshop, October 20-22, 2014
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PSU Completed Milestones: DOE Award DE-FE0005540, UTSR Project 07-01-SR127
Measure Endwall Overall Effectiveness Completed Q8
Measure Endwall Overall Effectiveness with Deposits Completed Q10
Measure Endwall Overall Effectiveness with TBC Completed Q11
Computational Predictions of Conjugate Heat Transfer, with and without TBC
Completed Q12
Measure Overall Effectiveness with Optimized Endwall Design (Contoured)
Completed Q13
Measure Contoured Endwall Overall Effectiveness with TBC
Completed Q14
Measure Velocity Fields with and without Film Cooling Completed Q14
Computational Predictions of Contoured Endwall Conjugate Heat transfer, with and without TBC
Completed Q16
Supplementary Tasks (not in original proposal)
Fla
t E
nd
wa
ll
Co
nto
ure
d
2
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3
Better understanding of endwall cooling and its interaction with endwall contouring is needed to predict performance
air
ax
k
hCNu
Heat Transfer
Coefficients
Metal
Temp.
Design
Codes
exitc,
aw
TT
TTη
Adiabatic Wall
Temperature
Praisner et al. [2007] – Pack-B contour
Lynch et al. [2011]
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Conjugate heat transfer measurements and predictions of flat and contoured endwalls will be presented
Contoured Endwall Effectiveness and Flow Measurements
Endwall Effectiveness with TBC
Overall Effectiveness with Deposition
Flat Endwall Overall Effectiveness
4
φTBC
φ
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Matched Parameters
Typical Engine Model
Re∞,in (Cax) 1.25 x 105 1.25 x 105
h∞/hi 1 0.5 - 2.3
M = (ρcUc/ρ∞U∞) 1 – 2 0.6, 1, 2
Bi∞ = h∞t/kw 0.27 0.30 - 0.77
Overall effectiveness (metal temperature)
Matching the geometry, Biot number and h∞/hi to engine conditions allows direct measurement of metal temperature
geometryM,Re,fχη
Blade
tw
Tc,in
T∞ φ, Tw
Impingement plate
Corian Endwall, kw
hi
h∞
χη, Tfilm χηhhBi1
χη-1
TT
TTφ
iinc,
w
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Mainstream flow is heated, and coolant flow is chilled to maximize driving ΔT = T∞-Tc,internal
Wind Tunnel Side View
Plenums Tc,in~14°C Heat Exchanger
Auxiliary
Chiller
Des
icca
nt
Dri
er
T∞ ~ 54°C
Chilled air section of wind tunnel
Coolant Blower
LFE
Test Section
Heated Mainstream
Flow
Coolant Flow
6
5
4
3
2
1
Test Section Top View
Corian®
Film and impingement cooling
Only
impingement
cooling
Only film cooling
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endwall thermocouples
PS
x
y
SS D = 4.4 mm
Thermocouples were installed on the endwall surface under the TBC to measure φTBC along two streamlines
Film cooling holes, 30°
P/D = 4.7
S/D = 4.7
Top view of endwall within the passage
Incoming Flow Direction
Exit Flow
Direction
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in-hole convection
exiting coolant
uniform high effectiveness
The measurements of overall effectiveness demonstrated the key features of film cooling and internal impingement
Mavg = 2.0 inc,
w
TT
TTφ
Combined Film and Impingement, φ
Film Cooling Only, φf
Impingement Cooling Only, φo
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9
Increasing blowing ratio improved average φ for impingement more than for film cooling
Area
Averaged x
y
0.0
6
0.1
7
0.2
2
0.3
9
0.6
1
x/Cax =
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
-0.2 0.0 0.2 0.4 0.6 0.8 1.0
Lat. Avg. Film Cooling, f
Lat. Avg. Impingement, o
Lat. Avg. Film and Impingement, Lat. Avg. Film and Impingement, , repeat
x/Cax
Mavg = 1.0
0.0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.5 1.0 1.5 2.0
Measured Area Avg. Film Cooling, f
Measured Area Avg. Impingement, o
Measured Area Avg. Film and Impingement, Predicted Area Avg. Film and Impingement,
Mavg
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Conjugate RANS simulations used the SST k-ω model and an unstructured computational grid with wall prism layers
Grid
Surfaces Velocity inlet
Periodic boundaries
Blade
Plenum
Outflow y
x z
Conducting endwall
Adiabatic Adiabatic
TBC grid, 0.3 M cells
Endwall grid, 1.5 M cells
Impingement plate
Endwall
Blade
y z
FLUENT – SIMPLE RANS, SST k-ω, & energy – 2nd order Flow grid – 9.8 M cells y+ < 1 Flow and solid domains thermally coupled
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There is good overall agreement between the measured and predicted φ, except for the attachment of the jets
inc,
wTBC
TT
TTφφ,
Measured Tw Predicted Tw
Mavg = 1.0 Mavg = 2.0
Measured Tw Predicted Tw
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CFD temperature results show the three-dimensional conduction and steep gradients within the endwall
Velocity Magnitude inc,ΤΤ
ΤΤ
plenum
x/Cax = 0
1st row of impingement holes
x
y
viewing direction
y
z mainstream
plenum imp. plate
endwall y z
x/Cax = 0.09
2nd row of impingement holes
viewing direction
x y
Mavg = 1.0
Mavg = 2.0
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We simulated deposition with wax, matching the Stokes number, Thermal Scaling Parameter and conductivity ratio
6.54Lμ 18
Udρ
scale time fluid
time relaxation particleStk
c
p2pp
0.3UL
ttTSP
i,
21
1220
1240
1260
1280
1300
1320
0.0001 0.001 0.01 0.1 1 10
10m Fly Ash
Fly
As
h P
art
icle
Te
mp
era
ture
(C
)
Tinitial
=
Tsolid
= 1260oC
Tgas
=
Particle Phase
t1 t2
i,UL
t
TSP < 1 Solid
TSP > 1 Molten
9.1 Cax upstream
0.069k
k
wall
deposit 0.11
k
k
Corian
wax
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The cooling systems mitigated some deposition, but effectiveness was reduced everywhere in the passage
orinc,
w
TT
TTφ
inc,
wax
TT
TTω
Post deposition, w
No deposition, φ Post deposition, ω
Passage inlet
Mavg = 1.0
φ, Tw ω, Twax
tdep h∞
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15
We observed clear areas due to the film cooling jets, and deposition on the blade from the passage vortex
intc,
fw,f
TT
TTφ
intc,
fwax,f
TT
TTω
Evidence of
passage vortex
Post deposition, wf
No deposition, f
Mavg = 1.0
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Roughness from the deposition degrades the cooling performance, resulting in higher endwall temperatures
0.0
0.1
0.2
0.3
0.4
0.5
0.6
i, Mavg = 0.6
i,dep, Mavg = 0.6 w/ deposition
i, Mavg = 1.0
i,dep, Mavg = 1.0 w/ deposition
i, i,dep
Film Only Film & Impingement
Mavg = 0.6 Mavg = 1.0 Mavg = 0.6 Mavg = 1.0
i i,dep
h∞ increased by 30-100%
with deposition
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0.0
0.1
0.2
0.3
0.4
0.5
0.0 2.0 4.0 6.0 8.0 10.0 12.0
meas, Mavg = 1
pred, Mavg = 1
meas, Mavg = 2
pred, Mavg = 2
NuD,i,pred, Mavg = 1
NuD,i,pred, Mavg = 2
0
3
6
9
12
15
H/D
NuD,i
Although the Nu peaks at H/D = 2.9, the area averaged φ, with film and impingement, is relatively insensitive to H/D
H/D = 0.6
H/D = 2.9 (nominal)
0.0
0.1
0.2
0.3
0.4
0.5
0.0 2.0 4.0 6.0 8.0 10.0 12.0
meas, Mavg = 1
pred, Mavg = 1
meas, Mavg = 2
pred, Mavg = 2
H/D
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Contouring reduces effectiveness for impingement only, since hi decreases and h∞ increases from the flat endwall
0.0
0.1
0.2
0.3
0.4
0.5
-0.2 0.0 0.2 0.4 0.6 0.8 1.0
Flat, Mavg = 0.6Flat, Mavg = 1.0
Flat, Mavg = 2.0
Contoured, Mavg = 0.6Contoured, Mavg = 1.0
Contoured, Mavg = 2.0
o
x/Cax
Impingement Cooling Only
Flat Contoured
M = 2.0
Lynch et al. [2011]
flat
flatcontour
h
hh
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0.0
0.1
0.2
0.3
0.4
0.5
-0.2 0.0 0.2 0.4 0.6 0.8 1.0
Flat, Mavg = 0.6
Flat, Mavg = 1.0
Flat, Mavg = 2.0
Contoured, Mavg = 0.6
Contoured, Mavg = 1.0
Contoured, Mavg = 2.0
x/Cax
Film and Impingement Cooling
Overall effectiveness does not change much between the flat and contoured endwall with film cooling
0
0.1
0.2
0.3
0.4
-0.2 0.0 0.2 0.4 0.6 0.8 1.0
f
x/Cax
Film Cooling Only Flat Contoured
Film Cooling
Only, M = 2.0
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Although the average overall effectiveness is the same for the flat and contoured endwall, there are local differences
inc,
w
TT
TTφ
Flat Measured φ Flat Measured φ Contoured Measured φ
Contoured Measured φ
Mavg = 1.0 Mavg = 2.0
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Other than film attachment, the contoured endwall simulations predict the same trends as the measurements
inc,
w
TT
TTφ
Measured Tw Measured Tw Predicted Tw Predicted Tw
Mavg = 1.0 Mavg = 2.0
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The trailing edge flowfield was measured using a time resolved particle image velocimetry (PIV) system
Flowfield was sampled for 3000 or 6000 images at Δt = δ/U∞
U(t), V(t) t
t +Δt
Cross correlation
LaVision
Double pulsed laser
Blade
Light sheet Blade
flow
High speed camera
Image 1
Image 2
interrogation window = .035D ≈ 4δ
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Plane C
Pla
ne
C
3D
5D U∞,in
y/C
ax
x/Cax
The trailing edge flowfield was measured for three vertical planes to capture the passage vortex development
1.08Cax
30°
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Pla
ne
C
Mavg = 2.0
Plane A Plane B
Plane C
Endwall Endwall
Trai
ling
Edge
Trai
ling
Edge
Endwall
Trai
ling
Edge
Endwall Endwall Endwall
z = 0
z = 0
U/U∞,in
z = 0.32S
z = 0.32S
The passage vortex, indicated by the low velocity region, moves farther away from the wall with film cooling
No Film Cooling
24
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Pla
ne
C
Mavg = 2.0
Plane A Plane B
Plane C
Endwall Endwall
Trai
ling
Edge
Trai
ling
Edge
Endwall
Trai
ling
Edge
Endwall Endwall Endwall
z = 0.32S
z = 0.32S
z = 0
z = 0
Contours of turbulent kinetic energy show two bands of peak tke, indicating the presence of two vorticies
25
TKE/U∞,in2
No Film Cooling
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Matched Parameters
Typical Engine Model
Re∞,in (Cax) 1.25 x 105 1.25 x 105
h∞/hi 1 0.5 - 2.3
M = (ρcUc/ρ∞U∞) 1 – 2 0.6, 1, 2
Bi∞ = h∞t/kw 0.27 0.30 - 0.77
0.6–9.3 2.5
χη
1RRBi
hhBi1
χη-1
TT
TTφ
wTBC
iinc,
wTBC
Overall effectiveness with TBC
To accurately quantify the thermal effect of TBC, the thermal resistance was scaled to match the engine
TBCw
wTBC
w
TBC
kt
kt
R
R
Blade
tw
Tc,in
T∞ φTBC, Tw
Impingement plate
τ, TTBC TBC
Corian Endwall, kw
hi
h∞
inc,
TBC
TT
TTτ
geometryM,,Refχη
TBC effectiveness
cork
26
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The conjugate simulations predict significant and uniform cooling with TBC for the flat endwall
Mavg = 1.0
inc,
wTBC
TT
TTφφ,
With TBC - Predicted Tw
Mavg = 2.0
No TBC -Predicted Tw
0.19φflat 0.32φflat
0.22φflat 0.39φflat
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The conjugate simulations predict similar improvements with TBC for the contoured endwall with small differences
Mavg = 1.0
inc,
wTBC
TT
TTφφ,
With TBC - Predicted Tw
Mavg = 2.0
No TBC -Predicted Tw
0.19φflat 0.33φflat
0.38φflat 0.22φflat
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-0.5 0.0 0.5 1.0 1.5
Flat TBC Flat Contoured TBC Contoured
s/Cax
SS, Mavg = 1.0
-0.5 0.0 0.5 1.0 1.5
s/Cax
SS, Mavg = 2.0
0.0
0.2
0.4
0.6
0.8
1.0
-0.5 0.0 0.5 1.0 1.5
,
TBC
s/Cax
SS, Mavg = 0.6
Endwall contouring measurements along the streamlines are similar to the flat endwall, with and without TBC
PS
SS
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Adding TBC improves φ more than an increase in blowing ratio because TBC reduces heat transfer
0.05ΔφM
0.15φφΔφ TBCTBC w
TBCw,wr
q
qqΔq
Net Heat Flux Reduction – outer endwall surface
also increases with M
x
y PS
SS
TBCΔφ
0
0.05
0.1
0.15
0.2
0.25
0.3
Measured flat improvement w/ TBC
Predicted flat improvement w/ TBC
Predicted flat qr w/ TBC
Measured cont improvement w/ TBC
Predicted cont improvement w/ TBC
Measured contoured qr w/ TBC
0
0.1
0.2
0.3
0.4
0.5
0.5 1.0 1.5 2.0
TBC
Mavg
qr
0
0.05
0.1
0.15
0.2
0.25
0.3
Measured flat improvement w/ TBC
Predicted flat improvement w/ TBC
Predicted flat qr w/ TBC
0
0.1
0.2
0.3
0.4
0.5
0.5 1.0 1.5 2.0
TBC
Mavg
qr
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Flat Measured, Mavg = 2.0
TBC temperature is less affected by the internal cooling and more affected by the film cooling performance
inc,
TBC
TT
TTτ
Flat Measured, Mavg = 1.0
TBC
Tc,in
T∞
τ , TTBC
endwall
Contoured Measured, Mavg = 2.0
Contoured Measured, Mavg = 1.0
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This study demonstrates conjugate heat transfer trends for gas turbine endwalls and the secondary flow effects
Measured φ
Good agreement between conjugate measurements and CFD predictions
Predicted φ
Demonstrate trends for:
Cork - TBC
Contouring
Deposition
Unique flowfield measurements demonstrate interactions between passage vortex and film cooling
Temperature gradients Turbulent
Kinetic
Energy
with TBC with film
cooling