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TECHNICAL PAPERS

Modeling Shrouded Stator Cavity Flows in Axial-Flow Compressors

[+] Author and Article Information
S. R. Wellborn, I. Tolchinsky

Rolls-Royce Allison, Indianapolis, IN 46206

T. H. Okiishi

Iowa State University, Ames, IA 50011

J. Turbomach 122(1), 55-61 (Feb 01, 1999) (7 pages) doi:10.1115/1.555427 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Wellborn, S. R., and Okiishi, T. H., 1996, “Effects of Shrouded Stator Cavity Flows on Multistage Axial Compressor Aerodynamic Performance,” NASA CR 198536, Oct.
Jefferson, J. L., and Turner, R. C., 1958, “Some Shrouding and Tip Clearance Effects in Axial Flow Compressors,” International Ship Building Progress, Vol. 5, pp. 78–101.
Wisler, D. C., 1988, Advanced Compressor and Fan Systems, GE Aircraft Engines, Cincinnati, OH (also 1986 Lecture to ASME Turbomachinery Institute, Ames, IA).
LeJambre,  C. R., Zacharias,  R. M., Biederman,  B. P., Gleixner,  A. J., and Yetka,  C. J., 1998, “Development and Application of a Multistage Navier–Stokes Flow Solver, Part II: Application to a High-Pressure Compressor Design,” ASME J. Turbomach., 120, pp. 215–223.
Heidegger, N. J., Hall, E. J., and Delaney, R. A., 1996, “Parameterized Study of High-Speed Compressor Seal Cavity Flow,” AIAA Paper No. 96–2807.
Ozturk, H. K., Childs, P. R. N., Turner, A. B., Hannis, J. M., and Turner, J. R., 1998, “A Three-Dimensional Computational Study of Windage Heating Within an Axial Compressor Stator Well,” ASME Paper No. 98-GT-119.
Chupp, R. E., Holle, G. F., and Scott, T. E., 1986, “Labyrinth Seal Analysis, Vol. IV—User Manual for the Labyrinth Seal Design Model,” Allison Gas Turbine, Division of General Motors Corporation, Indianapolis, IN. Jan. (also AFWAL-TR-85-2103, Vol. IV).
Tipton, D. L., Scott, T. E., and Vogel, R. E., 1986, “Labyrinth Seal Analysis, Vol III—Analytical and Experimental Development of a Design Model for Labyrinth Seals,” Allison Gas Turbine, Division of General Motors Corporation, Indianapolis, IN, Jan. (also AFWAL-TR-85-2103, Vol. IV).
McGreehan, W. F., and Ko, S. H., 1989, “Power Dissipation in Smooth and Honeycomb Labyrinth Seals,” ASME Paper No. 89-GT-220.
Adamczyk,  J. J., Mulac,  R. A., and Celestina,  M. L., 1986, “A Model for Closing the Inviscid Form of the Average-Passage Equation System,” ASME J. Turbomach., 108, pp. 180–186.
Adamczyk, J. J., 1985, “Model Equation for Simulating Flows in Multistage Turbomachinery,” ASME Paper No. 85-GT-220.
Celestina,  M. L., Mulac,  R. A., and Adamczyk,  J. J., 1986, “A Numerical Simulation of the Inviscid Flow Through a Counterrotating Propeller,” ASME J. Turbomach., 108, pp. 187–194.
Mulac,  R. A., and Adamczyk,  J. J., 1992, “The Numerical Simulation of a High-Speed Axial Flow Compressor,” ASME J. Turbomach., 114, pp. 517–5277.
Shabbir, A., Zhu, J., and Celestina, M. L., 1996, “Assessment of Three Turbulence Models in a Compressor Rotor,” ASME Paper No. 96-GT-198.
Adamczyk, J. J., Hathaway, M. D., Shabbir, A., and Wellborn, S. R., 1998, “Numerical Simulation of Multi-Stage Turbomachinery Flows,” presented at AGARD Applied Vehicle Technology Panel Symposium on Design Principles and Methods for Aircraft Gas Turbine Engines, Toulouse, France, May 11–15.
Mahler, F. H., 1972, “Advanced Seal Technology,” Pratt and Whitney Aircraft Division Tech. Rep. PWA-4372, Feb. (also AFAPL TR-72-8).
Ludwig, L., 1978, “Gas Path Sealing in Turbine Engines,” Seal Technology in Gas Turbine Engines, AGARD, AGARD Publications, Neuilly Sur Seine France, Apr. (also NASA TM 73890).
Stocker, H. L., Cox, D. M., and Holle, G. F., 1977, “Aerodynamic Performance of Conventional and Advanced Design Labyrinth Seals With Solid-Smooth, Abradable, and Honeycomb Lands,” NASA CR-135307, Nov.

Figures

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Variation in stage matching between builds 1 and 2 of the compressor
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Schematic of shrouded stator cavity flow model
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Representative straight-through seal cavity
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Schematic of seal-teeth geometric parameters
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Predicted and measured differences in pressure rise for stages 7–12. The filled circles denote the difference in pressure rise between build 2 and build 1. The open circles represent the difference in pressure rise between the double and nominal tip clearance simulation.
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Predicted and measured differences in pressure rise for stages 7–12. The filled circles denote the difference between build 2 and build 1. The open circles represent the difference between the double and nominal seal clearance simulation, while the open triangles represent the difference between the triple and nominal seal clearance simulation.
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Normalized distributions of rotor 11 discharge total pressure and total temperature
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Measured levels of seal-tooth clearance from the tear-down of build 2
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Measured and predicted hub total temperature data given as a difference from design intent

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