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US 2013/0276459 A1Published application
Resistive band for turbomachine blade
AssigneeGeneral Electric Company
InventorsHerbert Chidsey Roberts, Glenn Curtis Taxacher
Life of this patent
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Abstract
A turbomachine system includes a rotor that defines a longitudinal axis of the turbomachine system. A first blade is coupled to the rotor, and the first blade has first and second laminated plies. A first band is coupled to the first blade and is configured to resist separation of the first and second laminated plies.
Claims20
A system, comprising:
- a turbomachine, comprising:
- a rotor defining a longitudinal axis of the turbomachine;
- a first blade coupled to the rotor, wherein the first blade comprises first and second laminated plies;
- and
- a first resistive band coupled to the first blade and configured to resist separation of the first and second laminated plies.
2 more elements
An apparatus, comprising:
- A turbomachine blade configured mount within a fluid path of a turbomachine;
- and
- a resistive band coupled to the turbomachine blade and configured to resist separation of the turbomachine blade.
A gas turbine engine, comprising:
- a compressor having a plurality of compressor blades and configured to compress air;
- a combustor configured to receive the compressed air from the compressor and to combust a mixture of compressed air and fuel into combustion products;
- a turbine having a plurality of turbine blades and configured to receive the combustion products from the combustor;
- and
- a resistive band coupled to a first blade of the plurality of compressor blades or the plurality of turbine blades, wherein the first blade comprises first and second laminated plies, and the resistive band is configured to resist separation of the first and second laminated plies.
2 more elements
Dependencies are inferred from the claim text.