The aircraft engine operates in various conditions. In consequence, the design of seals must take account of the seal clearance changes and the risk of rubbing. A small radial clearance of the rotor tip seal leads to the honeycomb rubbing in take-off conditions, and the leakage flow may increase in cruise conditions. The aim of this study is to compare two honeycomb seal configurations of the low-pressure gas turbine rotor. In the first configuration, the clearance is small and rubbing occurs. In the second,—the fins of the seal are shorter to eliminate rubbing. It is assumed that the real clearance in both configurations is the same. A study of the honeycomb geometrical model is performed to reduce the computational effort. The problem is investigated numerically using the RANS equations and the two-equation k–ω SST turbulence model. The honeycomb full structure is taken into consideration to show details of the fluid flow. Main parameters of the clearance and leakage flows are compared and discussed for the rotor different axial positions. An assessment of the leakage flow through the seal variants could support the design process.
Skip Nav Destination
Article navigation
January 2017
Research-Article
Influence of Honeycomb Rubbing on the Labyrinth Seal Performance
Daniel Frączek,
Daniel Frączek
Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
e-mail: dfraczek@polsl.pl
Silesian University of Technology,
Gliwice 44-100, Poland
e-mail: dfraczek@polsl.pl
Search for other works by this author on:
Włodzimierz Wróblewski,
Włodzimierz Wróblewski
Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
Silesian University of Technology,
Gliwice 44-100, Poland
Search for other works by this author on:
Krzysztof Bochon
Krzysztof Bochon
Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
Silesian University of Technology,
Gliwice 44-100, Poland
Search for other works by this author on:
Daniel Frączek
Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
e-mail: dfraczek@polsl.pl
Silesian University of Technology,
Gliwice 44-100, Poland
e-mail: dfraczek@polsl.pl
Włodzimierz Wróblewski
Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
Silesian University of Technology,
Gliwice 44-100, Poland
Krzysztof Bochon
Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
Silesian University of Technology,
Gliwice 44-100, Poland
1Corresponding author.
Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received April 12, 2016; final manuscript received July 7, 2016; published online August 16, 2016. Editor: David Wisler.
J. Eng. Gas Turbines Power. Jan 2017, 139(1): 012502 (10 pages)
Published Online: August 16, 2016
Article history
Received:
April 12, 2016
Revised:
July 7, 2016
Citation
Frączek, D., Wróblewski, W., and Bochon, K. (August 16, 2016). "Influence of Honeycomb Rubbing on the Labyrinth Seal Performance." ASME. J. Eng. Gas Turbines Power. January 2017; 139(1): 012502. https://doi.org/10.1115/1.4034183
Download citation file:
Get Email Alerts
Operation of a Compression Ignition Engine at Idling Load Under Simulated Cold Weather Conditions
J. Eng. Gas Turbines Power (August 2025)
In-Cylinder Imaging and Emissions Measurements of Cold-Start Split Injection Strategies
J. Eng. Gas Turbines Power (August 2025)
Effects of Lattice Orientation Angle on TPMS-Based Transpiration Cooling
J. Eng. Gas Turbines Power (September 2025)
Compressor Development for CO2-Based Pumped Thermal Energy Storage Systems
J. Eng. Gas Turbines Power (September 2025)
Related Articles
Numerical Investigations for Leakage and Windage Heating in Straight-Through Labyrinth Seals
J. Eng. Gas Turbines Power (January,2016)
Experimental Force Coefficients for a Fully-Partitioned Pocket Damper Seal and Comparison to Other Two Seal Types
J. Eng. Gas Turbines Power (May,2023)
Numerical Investigations on Leakage Performance of the Rotating Labyrinth Honeycomb Seal
J. Eng. Gas Turbines Power (June,2010)
Computational Fluid Dynamics Investigation of Brush Seal Leakage Performance Depending on Geometric Dimensions and Operating Conditions
J. Eng. Gas Turbines Power (March,2016)
Related Proceedings Papers
Related Chapters
Aerodynamic Performance Analysis
Axial-Flow Compressors
Antilock-Braking System Using Fuzzy Logic
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis