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

Claim 9:
10. A turbine engine comprising:
a primary airflow path;
a rotor;
a first airfoil assembly comprising:
a first platform having a first upper platform face at least partially defining the primary airflow path, the first airfoil assembly being radially spaced from the rotor to define a gap therebetween; and
a first airfoil extending from the first 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;

a second airfoil assembly comprising:
a second airfoil provided upstream of and axially adjacent the first airfoil; and
a second platform extending from the rotor;

a secondary airflow path at least partially defined by the gap between the first platform and the rotor, and the second platform; and
a deflector extending between an axially forward edge and an axially aft edge, the deflector being positioned within the secondary airflow path such that that the axially aft edge is upstream of the axially forward edge.