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Research Papers: Gas Turbines: Structures and Dynamics

Measurements of Leakage and Power Loss in a Hybrid Brush Seal

[+] Author and Article Information
Luis San Andrés

Mechanical Engineering Department, Texas A&M University, College Station, TX 77843lsanandres@mengr.tamu.edu

José Baker

Mechanical Engineering Department, Texas A&M University, College Station, TX 77843jbakerv@tamu.edu

Adolfo Delgado

Mechanical Engineering Department, Texas A&M University, College Station, TX 77843adelgam@tamu.edu

J. Eng. Gas Turbines Power 131(1), 012505 (Oct 10, 2008) (6 pages) doi:10.1115/1.2967497 History: Received April 01, 2008; Revised April 02, 2008; Published October 10, 2008

Simplicity, low cost, and easy replacement make labyrinth seals the primary seal type in gas turbines. However, excessive leakage and potential for rotordynamic instability are well known issues. Brush seals effectively control leakage in air breathing engines, albeit only applied for relatively low pressure differentials. Hybrid brush seals (HBSs) are an alternative to resolve poor reliability resulting from bristle tip wear while also allowing for reverse rotation operation. The novel configuration incorporates pads contacting the shaft, which under rotor spinning lifts off due to the generation of a hydrodynamic pressure. The ensuing gas film prevents intermittent contact, thus lowering the operating temperature and thermal distortions and even eliminating bristle wear. The hybrid brush seal improves sealing, is more durable and reliable than conventional brush seals, and allows reverse shaft rotation without seal damage. This paper presents measurements of power loss and leakage in a HBS for increasing pressure differentials over a range of rotor speeds. The test HBS, Haynes-25 bristle pack (850bristlescm) and 45 deg lay angle, is 166.4 mm in diameter and integrates 20-arcuate pads connected with thin electrical-discharge machined webs (EDM-webs) to the seal casing. The webs are designed with low radial stiffness to allow for rotor excursions and high axial stiffness to avoid pad pitching motions resulting from high pressure differentials across the seal. Measured drag power at low rotor speeds (<11ms at 1300 rpm) decreases as the pressure differential across the seal increases. At a fixed rotor speed, a significant drop in drag torque (and drag power) ensues as the supply pressure increases, thus demonstrating that a gas film separates the rotor from the seal pads. Additionally, the operating temperature measured at the rotor/seal interface remains approximately constant (24°C) during tests with shaft rotation (power loss and drag torque measurements) under pressurized conditions, indicating that the rotor and seal pads are not in contact. Flow rate measurements at room temperature (25°C) show an improved sealing ability with a leakage reduction of about 36% when compared with a first generation shoed-brush seal. The HBS calculated effective clearance (50μm) is approximately 70% smaller than the radial clearance (180μm) of an ideal noncontacting seal with similar rotor diameter. Improved brush seal technology will increase the efficiency of gas turbines while also aiding to improve the engine stability and to reduce vibrations.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Axial and cross-sectional views of conventional brush seal

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Figure 2

Close-up view of first generation SBS

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Figure 3

Close-up view of HBS

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Figure 4

Rotordynamic test rig for a HBS: (top) isometric view and (bottom) cross-sectional view

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Figure 5

Detailed view of disk/shaft assembly

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Figure 6

Schematic profile view of the HBS (not to scale)

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Figure 7

Test flow rates for first generation SBS and HBS versus supply to discharge pressure ratio under static conditions (no shaft rotation)

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Figure 8

Test flow rate for HBS versus rotor speed for increasing supply to discharge pressure ratios

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Figure 9

Calculated effective clearance for SBS and HBS versus supply pressure to discharge pressure ratio at static condition (no rotation) and selected shaft speeds (600 rpm and 1300 rpm)

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Figure 10

Test power loss for HBS versus rotational speed for increasing supply to discharge pressure ratios

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Figure 11

Drag torque for HBS versus rotational speed for increasing supply to discharge pressure ratios

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Figure 12

Surface profile of the disk along its axial span; estimation of wear after 10 h of operation (tests with shaft rotation)

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