US 11,905,853 B2
Turbine engine component with a set of deflectors
Alberto Buonvino, Turin (IT); Luca Giacobone, Turin (IT); Daniele Coutandin, Avigliana (IT); Ernesto Sozio, Orbassano (IT); and Francesco Bertini, Piossasco (IT)
Assigned to GE AVIO S.r.l., Rivalta di Torino (IT)
Filed by GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Apr. 13, 2021, as Appl. No. 17/228,778.
Claims priority of application No. 102020000013609 (IT), filed on Jun. 8, 2020.
Prior Publication US 2021/0381389 A1, Dec. 9, 2021
Int. Cl. F01D 9/04 (2006.01); F01D 5/14 (2006.01); F01D 11/00 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 5/14 (2013.01); F01D 5/141 (2013.01); F01D 11/001 (2013.01); F01D 11/006 (2013.01); F05D 2220/32 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01)] 16 Claims
OG exemplary drawing
 
1. An airfoil assembly defining a primary airflow path for a turbine engine, the airfoil assembly comprising:
a platform at least partially defining a secondary airflow path fluidly coupled to the primary airflow path, the platform having an upper platform face at least partially defining the primary airflow path;
an airfoil extending from the platform and into the primary airflow path, the airfoil having an airfoil outer wall defining an airfoil pressure side and an airfoil suction side; and
a deflector provided along a portion of the platform axially forward of the airfoil, the deflector extending into the secondary airflow path, the deflector having:
an axially forward edge provided within the secondary airflow path;
an axially aft edge provided upstream of the axially forward edge; and
a deflector wall defining a concave side and a convex side and extending between an axially forward edge and an axially aft edge;
wherein the deflector is oriented such that the concave side corresponds to the airfoil pressure side.