Cooling of a honeycomb seal in the part of a gas turbine to which hot gas is admitted
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United States of America Patent
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Jan 9, 2001
Grant Date -
N/A
app pub date -
Apr 16, 1999
filing date -
May 13, 1998
priority date (Note) -
Expired
status (Latency Note)
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Abstract
The present invention pertains to the cooling of a honeycomb seal (2), which is arranged in a carrier ring (4), with vertical (2.2) and horizontal (2.1) honeycomb openings. To achieve this, the support ring (4) of the honeycomb seal (2) is provided with cooling air grooves (5) and tangentially arranged cooling holes (6), so that the cooling air (7) is fed homogeneously from the outer annular chamber (8) to the honeycomb seal (2) and can escape via the open honeycomb structure (2.2). Intense cooling action of the honeycomb seal (2), which is subject to high thermal stress, is generated as a result. Furthermore, corrosive process gas is kept extensively away from the honeycomb seal (2). At the same time, the sealing effect of the rotor blade labyrinth seal is improved by the cooling air flow (7) and the rotor blade leak flow (11) crossing each other or being directed in opposite directions.
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