Dual source cooling air shroud arrangement for a gas turbine engine
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United States of America Patent
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Mar 20, 2018
Grant Date -
Nov 20, 2014
app pub date -
May 12, 2014
filing date -
May 14, 2013
priority date (Note) -
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Abstract
A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.
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