High temperature rotor blade attachment
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United States of America Patent
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-
Jan 26, 1999
Issued Date -
N/A
app pub date -
Jan 16, 1997
filing date -
Aug 1, 1995
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A lightweight high temperature rotor blade attachment structure for use in a gas turbine engine. The lightweight high temperature rotor blade attachment lug being cast of a single crystal alloy and the lug is then bonded to a conventional nickel based wheel. A circular arc firtree is utilized to connect the insertable turbine blade between a pair of circumferentially spaced lugs that have been bonded to the turbine disk. In an alternate form of the present invention the attachment lug includes an internal cooling passage for receiving cooling fluid from a compressor. More particularly, the present invention discloses a single crystal attachment lug that is bonded to a powdered metal nickel alloy rotor disk and includes internal cooling passages, and in one form is designed for use with turbine blades that do not have a platform. Further, in amother form of the present invention the single crystal attachment lug is bonded to the powdered metal nickel rotor disk and is designed to be used with turbine blades having a platform.
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