Patent ID: 8926283
Filing Date: 2015-01-06
Classification: F01D

Abstract:
1. A gas turbine engine, comprising: a plurality of blades assembled into an annular row of blades about a gas turbine engine longitudinal axis and partly defining both a hot gas path and a cooling fluid path, wherein the cooling fluid path extends from a rotor cavity, past a side of a radially inward base of the row of blades where the side is upstream with respect to a flow of hot gases in the hot gas path, and leads to the hot gas path; an angel wing assembly disposed on the side of the base of the row of blades; and a plurality of pumping features, each comprising a single pumping surface and a complementary surface, distributed about the angel wing assembly configured to impart, at a narrowest gap of the cooling fluid path defined by the angel wing, motion to a flow of cooling fluid flowing there through, wherein the plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion about the gas turbine engine longitudinal axis to the flow of cooling fluid as it enters the hot gas path, and wherein the single pumping surface and the complementary surface are disposed radially inward of and transverse to a radially outer surface of the angel wing assembly and circumferentially adjacent to each other.