Sealing arrangement on combustor to turbine interface in a gas turbine
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United States of America Patent
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Aug 25, 2020
Grant Date -
Jan 18, 2018
app pub date -
Jul 14, 2017
filing date -
Jul 15, 2016
priority date (Note) -
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Abstract
A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.
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