Turbine shroud segment with serpentine cooling channels having a bend passage
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United States of America Patent
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Jul 23, 1996
Grant Date -
N/A
app pub date -
Jan 31, 1995
filing date -
Jan 31, 1995
priority date (Note) -
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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 having a bend passage which includes a purge hole to avoid separating flow in the bend passage.
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