A previously verified axisymmetric Navier–Stokes computer code was extended for three-dimensional computation of eccentric rim seals of almost any configuration. All compressibility and thermal/momentum interaction effects are completely included, and the temperature, pressure, and Reynolds number of the mainstream, coolant stream, and turbine wheel are fixed at actual engine conditions. Regardless of the seal eccentricity, both ingress and egress are found between θ = −30 and 100 deg, which encompasses the location of maximum radial clearance at θ = 0 deg. All other θ locations within the rim seal show only egress, as does the concentric base case for all circumferential locations. Further, the maximum ingress occurs near θ = 30 deg for all eccentricities. This is found to produce a blade root/retainer temperature rise from the concentric case of 390 percent at 50 percent eccentricity and a 77 percent rise at 7.5 percent eccentricity. In addition, the nature of an increased eccentricity causing a decreased seal effectiveness is examined, along with the corresponding increase of cavity-averaged temperature.
Issue Section:
Research Papers
1.
Avva
R. K.
Ratcliff
M. L.
Leonard
A. D.
1989
, “CFD Analysis of Rotating Disk Flows
,” in: Recent Advances and Applications in Computational Fluid Dynamics, ASME
FED-Vol. 103
, pp. 99
–105
.2.
Avva, R., Smith, C., and Singhal, A., 1990, “Comparative Study of High and Low Reynolds Number Versions of k–ε Models,” Paper No. AIAA 90-0246.
3.
Baskharone, E., 1990, private communication.
4.
Chew
J. W.
1991
, “A Theoretical Study of Ingress for Shrouded Rotating Disk Systems With Radial Outflow
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 113
, pp. 91
–98
.5.
Dietzen, F. J., and Nordmann, R., 1986, “Finite Difference Analysis for the Rotordynamic Coefficients of Turbulent Seals in Turbopumps,” Proceedings of Rotordynamic Instability Problems in High Performance Turbomachinery, NASA CP-2443, Texas A&M University, pp. 269–284.
6.
Elovic, E., 1991, General Electric Co., public discussion during technical sessions, International Gas Turbine and Aeroengine Congress, Orlando, FL.
7.
Gosman, A. D., and Pun, W. M., 1974, “Calculations of Recirculating Flows,” Research Report, Report No. HTS/74/2, Department of Mechanical Engineering, Imperial College, London, United Kingdom.
8.
Hamabe, K., and Ishida, K., 1992, “Rim Seal Experiments and Analysis of a Rotor–Stator System With Nonaxisymmetric Main Flow,” ASME Paper No. 92-GT-160.
9.
Hendricks, R. C., 1993, NASA Lewis Research Center, public discussion during technical sessions, International Gas Turbine and Aeroengine Congress, Cincinnati, OH.
10.
Ivey, P., 1990, personal communication.
11.
Ivey, P., 1991, personal communication.
12.
Ko, S. H., and Rhode, D. L., 1990, “Derivation and Testing of a New Multiscale k–ε Turbulence Model,” Paper No. AIAA-90-0243.
13.
Ko
S. H.
Rhode
D. L.
1991
, “Thermal Details in a Rotor–Stator Cavity at Engine Conditions With a Mainstream
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 114
, pp. 446
–453
.14.
Ko, S. H., Rhode, D. L., and Guo, Z., 1993, “Computed Effects of Rim Seal Clearance and Cavity Width on Thermal Distributions,” ASME Paper No. 93-GT-419.
15.
Kamal
M. M.
1966
, “Separation in the Flow Between Eccentiric Rotating Cylinders
,” ASME Journal of Basic Engineering
, Vol. 88
, pp. 717
–724
.16.
Leonard
B. P.
1979
, “A Stable and Accurate Convective Modelling Procedure Based on Quadratic Upstream Interpolation
,” Computer Methods in Applied Mechanics and Engineering
, Vol. 19
, pp. 59
–98
.17.
Lowry, S. A., and Keeton, L. W., 1987, “Space Shuttle Main Engine High Pressure Fuel Pump Aft Platform Seal Cavity Flow Analysis,” NASA Technical Paper No. 2685.
18.
Owen, J. M., and Rogers, R. H., 1989, Flow and Heat Transfer in Rotating-Disc System: Vol. 1. Rotor–Stator Systems, Research Studies Press, Taunton.
19.
Patankar, S. V., 1980, Numerical Heat Transfer and Fluid Flow, McGraw-Hill, New York.
20.
Phadke
U. P.
Owen
J. M.
1988
, “Aerodynamic Aspects of the Sealing of Gas-Turbine Rotor–Stator Systems, Part 2: The Performance of Simple Seals in a Quasi-Axisymmetric External Flow
,” Int. J. Heat Fluid Flow
, Vol. 9
, No. 2
, pp. 106
–112
.21.
Pope
S. B.
1978
, “The Calculation of Turbulent Recirculation Flows in General Orthogonal Coordinates
,” Journal of Computational Physics
, Vol. 26
, pp. 197
–217
.22.
Rhode
D. L.
Demko
J. A.
Traegner
U. K.
Morrison
G. L.
Sobolik
S. R.
1986
, “Prediction of Incompressible Flow in Labyrinth Seals
,” ASME Journal of Fluids Engineering
, Vol. 108
, pp. 19
–25
.23.
Rhode
D. L.
Hensel
S. J.
Guidry
M. J.
1992
, “Labyrinth Seal Rotordynamic Force Using a Three-Dimensional Navier–Stokes Code
,” ASME JOURNAL OF TRIBOLOGY
, Vol. 114
, pp. 683
–689
.24.
Rhode
D. L.
Hensel
S. J.
Guidry
M. J.
1993
, “Three-Dimensional Computation of Rotordynamic Force Distributions in a Labyrinth Seal
,” STLE Tribology Transactions
, Vol. 36
, No. 3
, pp. 461
–469
.25.
Sturgess, G. J., and Datta, P., 1988, “Calculation of Flow Development in Rotating Passages for Cooled Gas Turbine Blades,” ASME Paper No. 88-GT-XXX.
26.
Vaughan, C. M., and Turner, A. B., 1987, “Numerical Prediction of Axisymmetric Flow in a Rotor–Stator System With an External Mainstream Flow,” Proceedings 5th International Conference on Numerical Methods in Laminar and Turbulent Flows, Swansea, United Kingdom.
27.
Virr
G. P.
Chew
J. W.
Coupland
J.
1994
, “Application of Computational Fluid Dynamics to Turbine Disk Cavities
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 116
, pp. 701
–708
.28.
Williams
M.
Chen
W. C.
Bache
G.
Eastland
A.
1991
, “An Analysis Methodology for Internal Swirling Flow Systems With a Rotating Wall
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 113
, pp. 83
–90
.
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