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US 2023/0417147 A1Published application
Cold spray duct for a gas turbine engine
AssigneeGeneral Electric Company
InventorsApostolos Pavlos Karafillis, Eric Dean Jorgensen, Craig Douglas Young, Jonathan Harry Kerner, Leonardo Ajdelsztajn
Life of this patent
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Abstract
A component for a turbine engine may be formed by spraying particulate with a nozzle toward a substrate. The particulate may be deposited to form one or more annular layers and a reinforcing structure. The component may be a closed loop annular component having a reinforcing structure of specific dimensions enabled by the methods described.
Claims21
1-20. (canceled)
A closed loop annular component for a turbine engine, comprising:
- a reinforcing structure, comprising:
- a rib structure defining:
- a rib height;
- a rib width;
- and
- a rib spacing between adjacent ribs, the rib spacing less than or equal to 2.5 inches;
- a skin defining a skin thickness between adjacent ribs;
- and
- a plurality of annular layers, comprising:
- a first annular layer;
- and
- a second annular layer, wherein the skin thickness is defined at least in part by each of the first and second annular layers.
9 more elements
A component for a turbine engine, comprising:
- a reinforcing structure, comprising:
- a rib structure defining:
- a rib height;
- a rib width;
- and
- a rib spacing between adjacent ribs;
- a skin defining a skin thickness between adjacent ribs;
- and
- a plurality of annular layers, comprising:
- a first annular layer;
- and
- a second annular layer, wherein the skin thickness is defined at least in part by each of the first and second annular layers.
9 more elements
Dependencies are inferred from the claim text.