The complex flow field in a gas turbine combustor makes cooling the liner walls a challenge. In particular, this paper is primarily focused on the region surrounding the dilution holes, which is especially challenging to cool due to the interaction between the effusion cooling jets and high-momentum dilution jets. This study presents overall effectiveness measurements for three different cooling hole patterns of a double-walled combustor liner. Only effusion hole patterns near the dilution holes were varied, which included: no effusion cooling; effusion holes pointed radially outward from the dilution hole; and effusion holes pointed radially inward toward the dilution hole. The double-walled liner contained both impingement and effusion plates as well as a row of dilution jets. Infrared thermography was used to measure the surface temperature of the combustor liners at multiple dilution jet momentum flux ratios and approaching freestream turbulence intensities of 0.5% and 13%. Results showed that the outward and inward geometries were able to more effectively cool the region surrounding the dilution hole compared to the closed case. A significant amount of the cooling enhancement in the outward and inward cases came from in-hole convection. Downstream of the dilution hole, the interactions between the inward effusion holes and the dilution jet led to lower levels of effectiveness compared to the other two geometries. High freestream turbulence caused a small decrease in overall effectiveness over the entire liner and was most impactful in the first three rows of effusion holes.

References

References
1.
Scrittore
,
J. J.
,
Thole
,
K. A.
, and
Burd
,
S. W.
,
2007
, “
Investigation of Velocity Profiles for Effusion Cooling of a Combustor Liner
,”
ASME J. Turbomach.
,
129
(
3
), pp.
518
526
.
2.
Facchini
,
B.
,
Tarchi
,
L.
,
Toni
,
L.
, and
Ceccherini
,
A.
,
2010
, “
Adiabatic and Overall Effectiveness Measurements of an Effusion Cooling Array for Turbine Endwall Application
,”
ASME J. Turbomach.
,
132
(
4
), p.
041008
.
3.
Martin
,
D.
, and
Thorpe
,
S. J.
,
2012
, “
Experiments on Combustor Effusion Cooling Under Conditions of Very High Free-Stream Turbulence
,”
ASME
Paper No. GT2012-68863.
4.
Kakade
,
V. U.
,
Thorpe
,
S. J.
, and
Gerendas
,
M.
,
2012
, “
Effusion-Cooling Performance at Gas Turbine Combustor Representatitve Flow Conditions
,”
ASME
Paper No. GT2012-68115.
5.
Odgers
,
J.
, and
Son
,
N. N.
,
1975
, “
Film Cooling—The Effect of a Cold Jet Normal to the Coolant Layer
,” Winter Annual Meeting, Houston, TX, Nov. 3–Dec. 4, p. 7.
6.
Button
,
B. L.
,
1984
, “
Effectiveness Measurements for a Cooling Film Disrupted by a Single Jet
,”
Int. Commun. Heat Mass Transfer
,
11
(
6
), pp.
505
516
.
7.
Martiny
,
M.
,
Schulz
,
A.
,
Wittig
,
S.
, and
Dilzer
,
M.
,
1997
, “
Influence of a Mixing-Jet on Film Cooling
,”
ASME
Paper No. 97-GT-247.
8.
Ceccherini
,
A.
,
Facchini
,
B.
,
Tarchi
,
L.
,
Toni
,
L.
, and
Coutandin
,
D.
,
2009
, “
Combined Effect of Slot Injection, Effusion Array and Dilution Hole on the Cooling Performance of a Real Combustor Liner
,”
ASME
Paper No. GT-2009-60047.
9.
Facchini
,
B.
,
Maiuolo
,
F.
,
Tarchi
,
L.
, and
Coutandin
,
D.
,
2010
, “
Combined Effect of Slot Injection, Effusion Array and Dilution Hole on the Heat Transfer Coefficient of a Real Combustor Liner—Part 1: Experimental Analysis
,”
ASME
Paper No. GT-2010-22936.
10.
Andreini
,
A.
,
Caciolli
,
G.
,
Facchini
,
B.
,
Tarchi
,
L.
,
Coutandin
,
D.
,
Taddei
,
S.
, and
Peschiulli
,
A.
,
2012
, “
Density Ratio Effects on the Cooling Performances of a Combustor Liner Cooled by a Combined Slot/Effusion System
,”
ASME
Paper No. GT2012-68263.
11.
Vakil
,
S. S.
, and
Thole
,
K. A.
,
2005
, “
Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine
,”
ASME J. Eng. Gas Turbines Power
,
127
(
2
), pp.
257
267
.
12.
Scrittore
,
J. J.
,
Thole
,
K. A.
, and
Burd
,
S. W.
,
2005
, “
Experimental Characterization of Film-Cooling Effectiveness Near Combustor Dilution Holes
,”
ASME
Paper No. GT2005-68704.
13.
Scrittore
,
J. J.
,
2008
,
Experimental Study of the Effect of Dilution Jets on Film Cooling Flow in a Gas Turbine Combustor
,
Virginia Polytechnic Institute and State University
, Blacksburg, VA.
14.
Schroeder
,
R. P.
, and
Thole
,
K. A.
,
2016
, “
Effect of High Freestream Turbulence on Flowfields of Shaped Film Cooling Holes
,”
ASME J. Turbomach.
,
138
(
9
), pp.
1
10
.
15.
Williams
,
R. P.
,
Dyson
,
T. E.
,
Bogard
,
D. G.
, and
Bradshaw
,
S. D.
,
2013
, “
Sensitivity of the Overall Effectiveness to Film Cooling and Internal Cooling on a Turbine Vane Suction Side
,”
ASME J. Turbomach.
,
136
(
3
), p.
31006
.
16.
Mensch
,
A.
, and
Thole
,
K. A.
,
2013
, “
Overall Effectiveness of a Blade Endwall With Jet Impingement and Film Cooling
,”
ASME J. Eng. Gas Turbines Power
,
136
(
3
), p.
31901
.
17.
Incropera
,
F. P.
,
DeWitt
,
D. P.
,
Bergman
,
T. L.
, and
Lavine
,
A. S.
,
2007
,
Fundamentals of Heat and Mass Transfer
,
Wiley
, Hoboken, NJ.
18.
Hollworth
,
B. R.
, and
Dagan
,
L.
,
1980
, “
Arrays of Impinging Jets With Spent Fluid Removal Through Vent Holes on the Target Surface—Part 1: Average Heat Transfer
,”
J. Eng. Power
,
102
(
2
), pp.
393
402
.
19.
Leonetti
,
M.
,
Lynch
,
S.
,
O'Connor
,
J.
, and
Bradshaw
,
S.
,
2017
, “
Combustor Dilution Hole Placement and Its Effect on the Turbine Inlet Flowfield
,”
J. Propul. Power
,
33
(
3
), pp.
750
763
.
20.
Moffat
,
R. J.
,
1985
, “
Using Uncertainty Analysis in the Planning of an Experiment
,”
ASME J. Fluids Eng.
,
107
(
2
), pp.
173
178
.
21.
Figliola
,
R. S.
, and
Beasley
,
D. E.
,
2011
,
Theory and Design for Mechanical Measurements
,
Wiley
, Hoboken, NJ.
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