Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine
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United States of America Patent
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Issued Date -
Feb 13, 2014
app pub date -
Aug 8, 2013
filing date -
Aug 9, 2012
priority date (Note) -
Abandoned
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Abstract
A restraint mechanism for rotor blades of a turbo engine on a rotor disk having blade root receptacles for radial guidance of the rotor blades is disclosed. The restraint mechanism has a plurality of axial securing elements, each having at least one web for positioning in a blade root receptacle, such that each web has a retaining section at one end for establishing a form-fitting design to a mating brace of another axial securing element. A method for axially securing rotor blades on a rotor disk and a turbo engine are also disclosed.
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