US 11,933,188 B2
Method of manufacturing gas turbine engine element having at least one elongated opening
Marc Campomanes, Longueuil (CA); Orlando Scalzo, Montreal (CA); and Bruno Chatelois, Boucherville (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on May 13, 2021, as Appl. No. 17/319,578.
Application 17/319,578 is a division of application No. 14/338,480, filed on Jul. 23, 2014, granted, now 11,035,249.
Prior Publication US 2021/0277797 A1, Sep. 9, 2021
This patent is subject to a terminal disclaimer.
Int. Cl. B22F 3/00 (2021.01); B05B 12/20 (2018.01); B05D 3/12 (2006.01); B22F 3/12 (2006.01); B22F 3/22 (2006.01); B22F 3/24 (2006.01); B22F 3/26 (2006.01); B22F 5/00 (2006.01); F01D 25/14 (2006.01); B22F 5/10 (2006.01)
CPC F01D 25/14 (2013.01) [B05B 12/20 (2018.02); B05D 3/12 (2013.01); B22F 3/004 (2013.01); B22F 3/12 (2013.01); B22F 3/225 (2013.01); B22F 3/24 (2013.01); B22F 3/26 (2013.01); B22F 5/009 (2013.01); B22F 2003/247 (2013.01); B22F 2005/103 (2013.01); B22F 2999/00 (2013.01); F05D 2230/21 (2013.01); F05D 2230/22 (2013.01); F05D 2230/90 (2013.01); F05D 2240/11 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method of manufacturing a shroud segment for an aircraft engine, the method comprising:
providing a mold defining a mold cavity having a shape corresponding to the shroud segment, the mold cavity including a platform cavity shaped to define a platform of the shroud segment, the platform cavity having a mold surface corresponding to an inner surface of the platform of the shroud segment;
providing an insert extending partly through the platform cavity, the insert including a plurality of elongated pins extending in the platform cavity along and spaced apart from the mold surface;
injecting a powder injection molding feedstock into the mold cavity to obtain a green part with a platform portion through which at least part of the elongated pins extend;
disengaging the green part from the mold, including sliding the elongated pins out of the platform portion of the green part to define a plurality of elongated cooling passages in the platform of the shroud segment, the elongated cooling passages disposed radially between inner and outer surfaces of the platform portion;
debinding and sintering the green part to define the shroud segment; and
projecting a coating material on the inner surface of the platform of the shroud segment from a source, the coating material being projected while providing an obstruction between the source and open ends of the elongated cooling passages to prevent the coating material from reaching the open ends of the elongated cooling passages.