A new experimental friction factor model for a honeycomb surface was developed using a static seal tester. Three clearances and three lengths were tested for the seals, and Reynolds number ranged from 3000 to 49,000. It was found that the friction factor was a function of Reynolds number and seal clearance only. The clearance effect was dominant and the friction factor was found to increase with increased clearance. A new uncertainty analysis was developed for the experimental friction factor when calculating friction factor using Mach number curve fit. The entrance loss coefficient was found to be constant for both smooth and honeycomb seals. The entrance loss coefficient of Honeycomb seals was found to be 50 percent higher than that of smooth seals. [S0742-4787(00)02102-0]

Issue Section:
Technical Papers
Keywords:
friction, turbines, machine testing, Mach number, loss measurement, gases, testing
Topics:
Friction, Honeycomb structures, Mach number
1.
Kleynhans
,
G.
, and
Childs
,
D.
,
1997
, “
The Acoustic Influence of Cell Depth on The Rotordynamic Characteristics of Smooth-Rotor/Honeycomb Stator Annular Gas Seals
,”
ASME J. Eng. Gas Turbines Power
,
119
, No.
4
, pp.
949
–
957
.
2.
Elrod, D, Nicks, C., Childs, D., and Nelson, C., 1985, “A Comparison of Experimental and Theoretical Results for Rotordynamic Coefficients of Four Annular Gas Seals,” TRC-SEALS-5-85, Turbomachinery Laboratories Report, Texas A&M University, July 1985.
3.
Kleynhans, G. F., 1991, “A Comparison of Experimental Results and Theoretical Prediction of the Rotordynamic and Leakage Characteristics of Short L/D=1/6 Honeycomb and Smooth annular Pressure Seals,” TRC-SEAL-12-91 #346, Turbomachinery Laboratory Report, Texas A&M University, December 1991.
4.
Nelson
,
C. C.
,
1984
, “
Analysis for Leakage and Rotordynamic Coefficients of Surface-Roughened Tapered Annular Gas Seals
,”
ASME J. Tribol.
,
106
, pp.
927
–
934
.
5.
Nelson
,
C. C.
,
1985
, “
Rotordynamic Coefficients for Compressible Flow in Tapered Annular Seals
,”
ASME J. Tribol.
,
107
, pp.
318
–
325
.
6.
Deissler, R. G., 1953, “Analysis of Turbulent Heat Transfer and Flow in The Entrance Regions of Smooth Passages,” NACA TN 3016.
7.
Elrod
,
D.
,
Childs
,
D.
, and
Nelson
,
C.
,
1990
, “
An Annular Gas Seal Analysis Using Empirical Entrance and Exit Region Friction Factors
,”
ASME J. Tribol.
,
112
, No.
2
, pp.
245
–
258
.
8.
Ha
,
T. W.
, and
Childs
,
D. W.
,
1994
, “
Annular Honeycomb-Stator Turbulent Gas Seals Analysis Using a New Friction Factor Model Based on Flat Plate Tests
,”
ASME J. Tribol.
,
116
, pp.
352
–
360
.
9.
Shapiro, A. H. and Smith, R. D., 1948, “Friction Coefficients in the Inlet Length of Smooth, Rounded Tubes,” NACA Technical Note No. 1785.
10.
Zucrow, J. M., and Hoffman, J. D., 1976, “Gas Dynamics,” 1, Wiley, New York, NY.
11.
Ha
,
T. W.
,
Morrison
,
G. L.
, and
Childs
,
D. W.
,
1992
, “
Friction Factor Characteristics for Narrow Channels with Honeycomb Surfaces
,”
ASME J. Tribol.
,
114
, pp.
714
–
721
.
12.
Ha
,
T. W.
, and
Childs
,
D. W.
,
1992
, “
Friction Factor Data for Flat-Plate Tests of Smooth and Honeycomb Surface
,”
ASME J. Tribol.
,
114
, pp.
772
–
730
.
13.
DeOtte, R., Morrison, G. L., Nava, A., and Hess, J. C., 1994, “A study of Friction Factor in Channel Flow Between Plates with Highly Roughened Surfaces,” Fluid Machinery Forum, ASME Summer Meeting, Lake Tahoe, NV, 19–23 Jun.
14.
Kays, W. M., 1950, “Loss Coefficient for Abrupt Changes in Flow Cross Section with Low Reynolds Number Flow in Single and Multiple-Tube Systems,” ASME Trans., pp. 1067–1074.
15.
Benedict, R. P., Carlucci, N. A., and Swetz, S. D., 1966, “Flow Losses in Abrupt Enlargements and Contractions,” ASME J. Eng. Power, pp. 73–81.
16.
Coleman, H. W., and Steele, W. G., 1989, “Experimentation and Uncertainty Analysis for Engineers,” Wiley, New York, NY.
17.
Brown, K. K. 1996, “Assessment of the Experimental Uncertainty Associated with Regressions,” Ph.D. dissertation, Department of Mechanical and Aerospace Engineering, University of Alabama in Huntsville.
Copyright © 2000
 by ASME
You do not currently have access to this content.