Patent ID: 9631509
Date: 2017-04-25
CPC Classifications: F01D,F05D,F16J

Claim:
1. A rim seal arrangement for a gas turbine engine, comprising: a first seal face on a rotor component, a second seal face on a stationary annular rim centered about a rotation axis of the rotor component, the second seal face facing the first seal face and being spaced from the first seal face along an axial direction to define a seal gap, wherein the seal gap is located between a radially outer hot gas path and a radially inner rotor cavity, wherein the first seal face comprises a plurality of circumferentially spaced depressions thereon, each depression having a depth in an axial direction and extending along a radial extent of the first seal face between a radially outer end and a radially inner end of the depression, the plurality of depressions being configured to influence flow in the seal gap such that during rotation of the rotor component, fluid in the seal gap is pumped in a radially outward direction to prevent ingestion of a gas path fluid from the hot gas path into the rotor cavity, and wherein each depression has a surface that transitions from a generally convex leading surface to a generally concave trailing surface along a circumferential direction.