Patent ID: 11959393
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 16:
17. An airfoil assembly for a turbine engine, the airfoil assembly being rotatable about a rotational axis, the airfoil assembly comprising:
a platform having a surface terminating at an end wall provided along an axially forward portion of the surface;
a pair of circumferentially adjacent airfoils spaced a circumferential distance from one another, with each airfoil of the pair of circumferentially adjacent airfoils having an outer wall extending between a leading edge and a trailing edge to define a chord-wise direction and between a root and a tip in a span-wise direction, the outer wall defining a pressure side and a suction side;
a splitter circumferentially spaced from the airfoil to define a channel therebetween, with respect to the rotational axis; and
a trench at least partially formed within the channel and including a trench inlet provided along the end wall, the trench inlet extending circumferentially a distance that is less than the circumferential distance between the pair of circumferentially adjacent airfoils.