Patent ID: 11933193
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 9:
10. A gas turbine engine comprising:
a first airfoil including:
a pressure side, a suction side, a leading edge, a trailing edge, a root, and a tip, wherein the leading edge and the trailing edge define a stream-wise direction, wherein the root and the tip define a span-wise direction, and wherein a throat is defined by a minimum distance between the suction side of the first airfoil and a trailing edge of a second airfoil adjacent the suction side of the first airfoil, the throat defining a span-wise direction throat line on the suction side; and
a set of dimples on the suction side, each of the dimples of the set of dimples having a non-perforated section, wherein the set of dimples have a first density in an area between the span-wise direction throat line and the trailing edge, wherein the set of dimples have a second density in an area between the span-wise direction throat line and the leading edge, wherein the first density is greater than the second density.