US 11,781,437 B2
Cold spray duct for a gas turbine engine
Apostolos Pavlos Karafillis, Winchester, MA (US); Eric Dean Jorgensen, Upton, MA (US); Craig Douglas Young, Blanchester, OH (US); Jonathan Harry Kerner, Brookline, MA (US); and Leonardo Ajdelsztajn, Niskayuna, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 4, 2021, as Appl. No. 17/307,394.
Prior Publication US 2022/0356807 A1, Nov. 10, 2022
Int. Cl. F01D 9/06 (2006.01); B05D 1/12 (2006.01); F01D 25/24 (2006.01)
CPC F01D 9/06 (2013.01) [B05D 1/12 (2013.01); F01D 25/24 (2013.01); F05D 2230/31 (2013.01); F05D 2240/128 (2013.01); F05D 2260/606 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A method for forming a closed loop annular component of a turbine engine, the method comprising:
spraying, with a nozzle, a first particulate of a first material towards a substrate;
spraying, with the nozzle, a second particulate of a second material towards the substrate;
maintaining a spray distance and a spray angle between the nozzle and the substrate during spraying;
depositing the first particulate on the substrate to form a first annular layer; and
selectively depositing the second particulate on the first annular layer to form a reinforcing structure, the reinforcing structure defining a pattern spacing between corresponding deposits less than or equal to 2.5 inches, wherein at least one of the substrate or the nozzle are rotatable about an axis, and wherein the first particulate is deposited radially inboard of the substrate relative to the axis.