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

Claim 8:
9. A turbine engine comprising:
a primary airflow path;
an engine centerline;
a first airfoil assembly at least partially provided within a primary airflow path of the turbine engine, the first airfoil assembly being rotatable in a first rotational direction, the first 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;
a first airfoil extending from the platform and into the primary airflow path the first 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 first airfoil the deflector extending into the secondary airflow path, the deflector having deflector wall defining a concave side and a convex side, with the deflector being oriented such that the concave side corresponds to the airfoil pressure side of the first airfoil; and

a second airfoil assembly at least partially provided within the primary airflow path, the second airfoil assembly comprising a second airfoil provided upstream of and axially adjacent the first airfoil, the second airfoil assembly being rotatable in a second rotational direction that that is counter the first rotational direction.