Turbine shroud segment including a coating layer having varying thickness
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United States of America Patent
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-
Aug 8, 1995
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 includes a substrate and a coating layer having varying thickness. Various construction details are developed that provide minimal spalling of the coating layer during use of the shroud segment. In a particular embodiment, a shroud segment includes a coating layer that tapers towards the edges. The thickness tapers to a minimum thickness along the leading and trailing edges. Within the blade passing region of the shroud segment, the coating layer tapers towards the lateral edges to a thickness determined by the minimum thickness required for abrasive contact between the shroud segment and rotor blades. In another particular embodiment, the varying thickness of the coating layer is produced by forming the substrate with a concave surface, applying the coating, and subsequently machining back the coating layer to the desired dimensions.
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