Installation tool for assembling a rotor blade of a gas turbine engine fan assembly
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United States of America Patent
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Apr 13, 2010
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app pub date -
Feb 20, 2008
filing date -
Jun 20, 2003
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Abstract
A method enables rotor assembly for a gas turbine engine to be assembled. The method includes providing a plurality of rotor blades that each include a dovetail, providing a rotor disc that includes a plurality of dovetail slots spaced circumferentially about the disc, partially inserting each rotor blade dovetail into a respective rotor dovetail slot, and seating the plurality of rotor blades in the respective rotor dovetail slot substantially simultaneously using an annular blade installation tool.
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