Research Papers: Gas Turbines: Structures and Dynamics

Influence of Honeycomb Rubbing on the Labyrinth Seal Performance

[+] Author and Article Information
Daniel Frączek

Institute of Power Engineering and Turbomachinery,
Silesian University of Technology,
Gliwice 44-100, Poland
e-mail: dfraczek@polsl.pl

Włodzimierz Wróblewski, Krzysztof Bochon

Institute of Power Engineering and Turbomachinery,
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 139(1), 012502 (Aug 16, 2016) (10 pages) Paper No: GTP-16-1136; doi: 10.1115/1.4034183 History: Received April 12, 2016; Revised July 07, 2016

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.

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Fig. 1

Effective clearance of the honeycomb seal (basic configuration)

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Fig. 2

Relative change in the cross section area in the function of the fin geometry and position (basic configuration, s = 0.77 mm)

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Fig. 3

Definition of clearance parameters, case C1r: (a) upstream fin edge and (b) downstream fin edge

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Fig. 4

Geometry of the blade tip domain and the computational domain

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Fig. 5

Discharge coefficient versus the number of mesh nodes

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Fig. 6

Overview of the computational mesh: (a) entire mesh in the seal domain and (b) mesh in the region above the second fin

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Fig. 7

Parameter ζgeom for cruise conditions: (a) first fin and (b) second fin

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Fig. 8

Parameter distributions at cross section B: (a) axial component of velocity, (b) radial component of velocity, (c) cylindrical component of velocity, and (d) relative static pressure

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Fig. 9

Comparison of velocity distributions at the seal outlet for different pitches

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Fig. 10

2D velocity streamlines on the XY plane: (a) case C1 and (b) case C1r

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Fig. 11

Parameters along the leakage streamlines: (a) relative static pressure and (b) relative velocity

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Fig. 12

Parameters above the second fin: (a) relative static pressure and (b) relative velocity

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Fig. 13

2D velocity streamlines on the XY plane for the shifted rotor: (a) case D1 and (b) case D1r

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Fig. 14

Parameter ζgeom for the shifted rotor: (a) first fin and (b) second fin

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Fig. 15

Parameters along the leakage streamline: (a) relative static pressure and (b) relative velocity

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Fig. 16

Parameters above second fin: (a) relative static pressure and (b) relative velocity



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