Cold spray duct for a gas turbine engine
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.
1 . A closed loop annular component for a turbine engine, comprising:
a reinforcing structure having a triangular grid pattern, 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, wherein the skin thickness is less than 0.030 inches and the rib width is less than 0.040 inches; 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.
2 . The closed loop annular component of claim 1 , wherein the first annular layer and the second annular layer are formed of the same material.
3 . The closed loop annular component of claim 1 , wherein the rib width is defined at least in part by each of the first and second annular layers.
4 . The closed loop annular component of claim 1 , wherein the first annular layer defines more of the skin thickness than the second annular layer.
5 . The closed loop annular component of claim 1 , wherein the skin thickness is less than or equal to 0.025 inches and the rib width is less than or equal to 0.020 inches.
6 . The closed loop annular component of claim 1 , wherein the skin thickness is greater than or equal to the rib width.
7 . The closed loop annular component of claim 1 , wherein the reinforcing structure comprises an isogrid pattern.
8 . The closed loop annular component of claim 1 , wherein the reinforcing structure comprises an orthogrid pattern.
9 . The closed loop annular component of claim 1 , wherein the reinforcing structure comprises a bi-grid pattern.
10 . A component for a turbine engine, comprising:
a reinforcing structure having a triangular grid pattern, 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, wherein the skin thickness is less than 0.030 inches and the rib width is less than 0.040 inches; 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.
11 . The component of claim 10 , wherein the first annular layer and the second annular layer are formed of the same material.
12 . The component of claim 10 , wherein the rib width is defined at least in part by each of the first and second annular layers.
13 . The component of claim 10 , wherein the first annular layer defines more of the skin thickness than the second annular layer.
14 . The component of claim 10 , wherein the skin thickness is less than or equal to 0.025 inches and the rib width is less than or equal to 0.020 inches.
15 . The component of claim 10 , wherein the skin thickness is greater than or equal to the rib width.
16 . The component of claim 10 , wherein the reinforcing structure comprises an isogrid pattern.
17 . The component of claim 10 , wherein the reinforcing structure comprises an orthogrid pattern.
18 . The component of claim 10 , wherein the reinforcing structure comprises a bi-grid pattern.