The demand for cleaner, more efficient energy has driven the motivation for improving the performance standards for gas turbines. Increasing the combustion temperature is one way to get the best possible performance from a gas turbine. One problem associated with increased combustion temperatures is that particles ingested in the fuel and air become more prone to deposition with an increase in turbine inlet temperature. Deposition on aero-engine turbine components caused by sand particle ingestion can impair turbine cooling methods and lead to reduced component life. It is necessary to understand the extent to which particle deposition affects turbine cooling in the leading edge region of the nozzle guide vane where intricate showerhead cooling geometries are utilized. For the current study, wax was used to dynamically simulate multiphase particle deposition on a large scale showerhead cooling geometry. The effects of deposition development, coolant blowing ratio, and particle temperature were tested. Infrared thermography was used to quantify the effects of deposition on cooling effectiveness. Although deposition decreased with an increase in coolant blowing ratio, results showed that reductions in cooling effectiveness caused by deposition increased with an increase in blowing ratio. Results also showed that effectiveness reduction increased with an increase in particle temperature. Reductions in cooling effectiveness reached as high as 36% at M = 1.0.

References

References
1.
Okita
,
Y.
, 2010, Original IHI contract regarding geometric specifications and operating conditions for the staggered showerhead geometry.
2.
Polanka
,
M. D.
,
Witteveld
,
V. C.
, and
Bogard
,
D. G.
, 1999, “
Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part I: Stagnation Region and Near-Pressure Side
,” ASME Paper 99-GT-48.
3.
Ou
,
S.
, and
Rivir
,
R. B.
, 2001, “
Leading Edge Film Cooling Heat Transfer With High Free Stream Turbulence Using a Transient Liquid Crystal Image Method
,”
Int. J. Heat Fluid Flow
,
22
, pp.
614
623
.
4.
Gao
,
Z.
, and
Han
,
J. C.
, 2009, “
Influence of Film-Hole Shape and Angle on Showerhead Film Cooling Using PSP Technique
,”
ASME J. Heat Transfer
,
131
(
6
), p.
061701
.
5.
Wenglarz
,
R. A.
, and
Fox
,
R. G.
, 1990, “
Physical Aspects of Deposition From Coal-Water Fuels Under Gas Turbine Conditions
,”
ASME J. Eng. Gas Turbines Power
,
112
, pp.
9
14
.
6.
Richards
,
G. A.
,
Logan
,
R. G.
,
Meyer
,
C. T.
, and
Anderson
,
R. J.
, 1992, “
Ash Deposition at Coal-Fired Gas Turbine Conditions: Surface and Combustion Temperature Effects
,”
ASME J. Eng. Gas Turbines Power
,
114
, pp.
132
138
.
7.
Wenglarz
,
R. A.
, and
Wright
,
I. G.
, 2003, “
Alternate Fuels for Land-Based Turbines
,”
Proceedings of the Workshop on Materials and Practices to Improve Resistance to Fuel Derived Environmental Damage in Land-and Sea-Based Turbines,
Oct. 22–24, CO School of Mines, Golden, CO, pp.
4
-45 to 4-
64
.
8.
Smith
,
C.
,
Barker
,
B.
,
Clum
,
C.
, and
Bons
,
J.
, 2010, “
Deposition in a Turbine Cascade With Combusting Flow
,” ASME paper GT2010-22855.
9.
Lawson
,
S. A.
, and
Thole
,
K. A.
, 2009, “
The Effects of Simulated Particle Deposition on Film Cooling
,” ASME Paper GT2009-59109.
10.
Albert
,
J. E.
,
Keefe
,
K. J.
, and
Bogard
,
D. G.
, 2009, “
Experimental Simulation of Contaminant Deposition on a Film Cooled Turbine Airfoil Leading Edge
,” ASME Paper IMECE2009-11582.
11.
Lawson
,
S. A.
, and
Thole
,
K. A.
, 2010, “
Simulations of Multi-Phase Particle Deposition on Endwall Film-Cooling
,” ASME Paper GT2010-22376.
12.
Sreedharan
,
S. S.
, and
Tafti
,
D. K.
, 2009, “
Effect of Blowing Ratio on Syngas Flyash Particle Deposition on a Three-Row Leading Edge Film Cooling Geometry Using Large Eddy Simulations
,” ASME Paper GT2009-59326.
13.
Lynch
,
S. P.
,
Sundaram
,
N.
,
Thole
,
K. A.
,
Kohli
,
A.
, and
Lehane
,
C.
, 2009, “
Heat Transfer for a Turbine Blade with Non-Axisymmetric Endwall Contouring
,” ASME Paper GT2009-60185.
14.
Byerley
,
A. R.
, 1989, “
Heat Transfer Near the Entrance to a Film Cooling Hole in a Gas Turbine Blade
,” D. Phil. Thesis, Department of Engineering Science, University of Oxford, Oxford, UK.
15.
Meftah
,
A.
,
Brisard
,
F.
,
Constantini
,
J. M.
,
Dooryhee
,
E.
,
Hage-Ali
,
M.
,
Hervieu
,
M.
,
Stoquert
,
J. P.
,
Studer
,
F.
, and
Toulemonde
,
M.
, 1994, “
Track Formation in SiO2 Quartz and the Thermal-Spike Mechanism
,”
Phys. Rev. B
,
49
(
18
), pp.
12,457
12,463
.
16.
Colban
,
W.
,
Gratton
,
A.
,
Thole
,
K. A.
, and
Haendler
,
M.
, 2006, “
Heat Transfer and Film-Cooling Measurements on a Stator Vane with Fan-Shaped Cooling Holes
,”
ASME J. Turbomach.
,
128
, pp.
53
61
.
17.
Moffat
,
R. J.
, 1988, “
Describing the Uncertainties in Experimental Results
,”
Exp. Therm. Fluid Sci.
,
1
, pp.
3
17
.
You do not currently have access to this content.