TURBINE BLADE TIP
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United States of America Patent
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N/A
Issued Date -
Sep 20, 2012
app pub date -
Mar 17, 2011
filing date -
Mar 17, 2011
priority date (Note) -
Abandoned
status (Latency Note)
Importance
Abstract
A tip rail configured to reduce stress when formed from a single crystal alloy is disclosed. The tip rail may be formed from at least one single crystal alloy oriented in a low modulus direction such that a gap exists at a location where the axis of orientation is positioned at a 45 degree angle to the outer surface of the suction side to reduce stress on the tip rail. The tip rail may be separately formed from a generally elongated blade to which the tip rail is configured to be attached. The tip rail may form a leading edge region recess proximate to the leading edge between an inner edge of the tip rail on the suction side and an inner edge of the tip rail on the pressure side and may form a trailing edge region recess proximate to the trailing edge. The gap reduces stress during use operation of a gas turbine engine in which the tip rail is attached to a turbine airfoil.
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