Turbine shroud segment with serpentine cooling channels
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United States of America Patent
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-
Jan 23, 1996
Grant Date -
N/A
app pub date -
Mar 30, 1994
filing date -
Mar 30, 1994
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A turbine shroud segment for use in a gas turbine engine includes a serpentine channel along at least one axial edge of the segment. Various construction details are developed that disclose a channel for efficiently flowing cooling fluid through an axial edge of a shroud segment. In a particular embodiment, a turbine shroud segment includes a leading edge serpentine channel and a trailing edge serpentine channel. Both serpentine channels include ducts that extend to the serpentine channels from a point inward of adjacent retaining hooks. Cooling fluid flowing onto the outward surface of the segments flows through the ducts and along the serpentine channels to cool the leading and trailing edges of the segments.
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