Patent ID: 11905853
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
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.