A computational fluid dynamic (CFD) investigation is presented that provides predictions of the aerodynamic impact of uniform and nonuniform coatings applied to the leading edge of a compressor airfoil in a cascade. Using a NACA 65(12)10 airfoil, coating profiles of varying leading edge nonuniformity were added. A nonuniform coating is obtained when a liquid coating is applied to a surface with high curvature, such as an airfoil leading edge. The CFD code used, RVCQ3D, is a Reynolds averaged Navier–Stokes solver, with a -omega turbulence model. The code predicted that these changes in leading edge shape can lead to alternating pressure gradients in the first few percent of chord that create small separation bubbles and possibly early transition to turbulence. The change in total pressure loss and trailing edge deviation are presented as a function of a coating nonuniformity parameter. Results are presented over a range of negative and positive incidences and inlet Mach numbers from 0.6 to 0.8. A map is provided that shows the allowable degree of coating nonuniformity as a function of incidence and inlet Mach number.
Issue Section:
Research Papers
1.
Caguiat
, D. E.
, 2003, “Rolls Royce/Allison 501-K Gas Turbine Antifouling Compressor Coatings Evaluation
,” ASME J. Turbomach.
0889-504X, 125
(3
), pp. 482
–488
.2.
Schwartz
, L. W.
, 2003, personal communication, Nov. 28.3.
Schwartz
, L. W.
, and Weidner
, D. E.
, 1995 “Modeling of Coating Flows on Curved Surfaces
,” J. Eng. Math.
0022-0833, 29
(1
), pp. 91
–103
.4.
Eley
, R. R.
, and Schwartz
, L. W.
, 2002, “Interaction of Rheology, Geometry, and Process in Coating Flow
,” J. Coat. Technol.
0361-8773, 74
, pp. 43
–53
.5.
Reid
, L.
, and Urasek
, D. C.
, 1973, “Experimental Evaluation of the Effects of a Blunt Leading Edge on the Performance of a Transonic Rotor
,” ASME J. Eng. Power
0022-0825, 95
, pp. 199
–204
.6.
Roberts
, W. B.
, 1984, “Axial Compressor Performance Restoration by Blade Profile Control
,” ASME Paper No. 84-GT-232.7.
Roberts
, W. B.
, 1995, “Advanced Turbofan Blade Refurbishment Technique
,” ASME J. Turbomach.
0889-504X, 117
(4
), pp. 666
–667
.8.
Suder
, K. L.
, Chima
, R. V.
, Strazisar
, A. J.
, and Roberts
, W. B.
, 1995, “The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor
,” ASME J. Turbomach.
0889-504X, 117
(4
), pp. 491
–505
.9.
Kwon
, O. J.
, and Sankar
, L. N.
, 1997, “Numerical Simulation of the Flow About a Swept Wing With Leading Edge Ice Accretions
,” Comput. Fluids
0045-7930, 26
(2
), pp. 183
–192
.10.
Khalid
, M.
, Zhang
, S.
, and Chen
, S.
, 2002, “A Study of Aerodynamic Performance Degradation on Aerofoils and Aircraft Wings Due to Accreted Ice
,” Aeronaut. J.
0001-9240, 106
, pp. 9
–15
.11.
Huebsch
, W. W.
, and Rothmayer
, A. P.
, 2002, “Effects of Ice Roughness on Dynamic Stall
,” J. Aircr.
0021-8669, 39
(6
), pp. 945
–953
.12.
Tuck
, E. O.
, 1991, “A Criterion for Leading Edge Separation
,” J. Fluid Mech.
0022-1120, 222
, pp. 33
–37
.13.
Walraevens
, R. E.
, and Cumpsty
, N. A.
, 1995, “Leading-Edge Separation Bubbles on Turbomachine Blades
,” ASME J. Turbomach.
0889-504X, 117
(1
), pp. 115
–125
.14.
Tain
, L.
, 1998, “Compressor Leading Edges in Incompressible and Compressible Flows
,” Ph.D. dissertation, Cambridge University.15.
Huoxing
, L.
, Baojie
, L.
, Ling
, L.
, and Haokang
, J.
, 2003, “Effect of Leading-Edge Geometry on Separation Bubble on a Compressor Blade
,” ASME Paper No. GT2003-38217.16.
Gostelow
, J. P.
, and Walker
, G. J.
, 1991, “Similarity Behavior in Transitional Boundary Layers Over a Range of Adverse Pressure Gradients and Turbulence Levels
,” ASME J. Turbomach.
0889-504X, 113
(4
), pp. 617
–625
.17.
Gostelow
, J. P.
, Blunden
, A. R.
, and Walker
, G. J.
, 1994, “Effects of Free-Stream Turbulence and Adverse Pressure Gradients on Boundary Layer Transition
,” ASME J. Turbomach.
0889-504X, 116
(3
), pp. 392
–404
.18.
Gostelow
, J. P.
, 1984, Cascade Aerodynamics
, Pergamon
, Oxford, England
, pp. 238
–241
.19.
Mayle
, R. E.
, 1991, “The Role of Laminar-Turbulent Transition in Gas Turbine Engines
,” ASME J. Turbomach.
0889-504X, 113
(4
), pp. 509
–537
.20.
Walker
, G. J.
, 1993, “The Role of Laminar Turbulent Transition in Gas Turbine Engines: A Discussion
,” ASME J. Turbomach.
0889-504X, 115
(2
), pp. 207
–217
.21.
Malkiel
, E.
, and Mayle
, R. E.
, 1996, “Transition in a Separation Bubble
,” ASME J. Turbomach.
0889-504X, 118
(4
), pp. 752
–759
.22.
Solomon
, W. J.
, Walker
, G. J.
, and Gostelow
, J. P.
, 1996, “Transition Length Prediction for Flows With Rapidly Changing Pressure Gradients
,” ASME J. Turbomach.
0889-504X, 118
(4
), pp. 744
–751
.23.
Solomon
, W. J.
, Walker
, G. J.
, and Hughes
, J. D.
, 1999, “Periodic Transition on an Axial Compressor Stator: Incidence and Clocking Effect: Part II—Transition Onset Predictions
,” ASME J. Turbomach.
0889-504X, 121
(3
), pp. 408
–415
.24.
Johnson
, M. W.
, 2002, “Predicting Transition Without Empiricism or DNS
,” ASME J. Turbomach.
0889-504X, 124
(4
), pp. 665
–669
.25.
Drela
, M.
, and Giles
, M. B.
, 1987, “Viscous-Inviscid Analysis of Transonic and Low Reynolds Number Airfoils
,” AIAA J.
0001-1452, 25
(10
), pp. 1347
–1355
.26.
Sanz
, W.
, and Platzer
, M. F.
, 1998, “On the Navier-Stokes Calculation of Separation Bubbles With a New Transition Model
,” ASME J. Turbomach.
0889-504X, 120
(1
), pp. 36
–42
.27.
Tain
, L.
, and Cumpsty
, N. A.
, 2000, “Compressor Blade Leading Edges in Subsonic Compressible Flow
,” Proc. Inst. Mech. Eng., Part C: J. Mech. Eng. Sci.
0954-4062, 214
, pp. 221
–242
.28.
Hobson
, G. V.
, and Weber
, S.
, 2000, “Prediction of Laminar Separation Bubble Over a Controlled Diffusion Compressor Blade
,” ASME Paper No. 2000-GT-277.29.
Wilcox
, D. C.
, 1998, Turbulence Modeling for CFD
, 2nd ed., DCW Industries
, La Canada, CA
.30.
Elmstrom
, M. E.
, 2004, “Numerical Prediction of the Impact of Non-Uniform Leading Edge Coatings on the Aerodynamics Performance of Compressor Airfoils
,” MS thesis, Naval Postgraduate School, Monterey, CA.31.
Chima
, R. V.
, 1997, “GRAPE 2-D Grid Generator for Turbomachinery: User’s Manual and Documentation
,” Version 104.32.
Chima
, R. V.
, 1987, “Explicit Multigrid Algorithm for Quasi-Three-Dimensional Viscous Flows in Turbomachinery
,” J. Propul. Power
0748-4658, 3
(5
), pp. 397
–405
.33.
Chima
, R. V.
, Turkel
, E.
, and Schaffer
, S.
, 1987, “Comparison of Three Explicit Multigrid Methods for the Euler and Navier Stokes Equations
,” NASA
Report No. TM-88878.34.
Chima
, R. V.
, 1999, “RVCQ3D—Rotor Viscous Code Quasi-3-D: User’s Manual and Documentation
,” Version 303.35.
Cumpsty
, N. A.
, 1989, Compressor Aerodynamics
, Longman Scientific and Technical
, Melbourne, FL
, p. 162
.36.
Menter
, F. R.
, 1994, “Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications
,” AIAA J.
0001-1452, 32
(8
), pp. 1598
–1605
.37.
Lieblein
, S.
, 1965, “Experimental Flow in Two-Dimensional Cascades
,” Aerodynamic Design of Axial Flow Compressors: NASA SP-36
, revised, p. 190
.Copyright © 2011
by American Society of Mechanical Engineers
You do not currently have access to this content.
