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US 2015/0308276 A1Published application
Robust turbine blades
AssigneeGeneral Electric Company
InventorsChad Daniel KLEINOW, Nirsene Anna LANGENBRUNNER, Matthew Mark WEAVER
Life of this patent
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Abstract
Robust turbine blade designs that minimize damage to turbine blades during a tip rub event, guard against further tip recession, and improve the resiliency of turbine blades 24 are provided. This may be achieved through various blade tip 12 designs, such as a recessed tip 28 or a protruding tip 98. It may also be achieved by providing the blade tip, shroud, or both with an environmental barrier coating (EBC) 22 having an abradable or abrasive layer.
Claims21
A robust turbine blade, comprising;
- a ceramic matrix composite (CMC) turbine blade having a leading edge, a trailing edge, a blade tip and an opposed root end;
- said ceramic turbine blade being curved in at least one dimension between said leading edge and said trailing edge;
- said blade tip having one of a recessed tip and a protruding tip;
- and,
- one of an abradable layer and an abrasive layer disposed on said blade tip and being at least one of recessed or protruding.
2 more elements
A robust turbine blade, comprising:
- a ceramic matric composite (CMC) turbine blade having a geometrically shaped blade tip to increase mechanical hold with one of an abrasive or an abradable layer;
- said blade tip and said one of an abrasive layer and an abradable layer both being one of flat, protruding or recessed shaped.
The robust turbine blade, comprising:
- a ceramic matrix composite (CMC) turbine blade having a leading edge, a trailing edge a blade tip and an opposed root end;
- said CMC turbine blade defining an airfoil shape;
- said blade tip being substantially flat;
- one of an abradable layer and an abrasive layer disposed on said blade tip, said one of an abradable layer and an abrasive layer being substantially flat.
1 more element
Dependencies are inferred from the claim text.