Aft outer rim seal arrangement

摘要

An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.

主权项

1. An outer rim seal arrangement for a gas turbine engine, comprising:
an annular and stationary rim centered about a longitudinal axis of a rotor disc, extending fore and comprising a fore-end, a radially outward-facing surface, and a radially inward-facing surface; a lower angel wing extending aft from a base of a turbine blade and comprising an aft end disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap between a rotor cavity and an outer cavity; an upper angel wing extending aft from the base of the turbine blade and comprising an aft end disposed radially outward of the rim outward-facing surface to define an upper angel wing seal gap between the outer cavity and a hot gas path; guide vanes disposed on the rim inward-facing surface in the lower angel wing seal gap and configured to discourage flow through the lower angel wing seal gap and into the rotor cavity during operation of the gas turbine engine, an air supply passage providing fluid communication between the rotor cavity and a source of a cooling fluid at atmospheric pressure, and a preswirler disposed downstream of the blade, between the air supply passage and the rotor cavity, wherein when the blade is rotating during operation the rotation is effective to draw the cooling fluid from the source, through the air supply passage, and into the rotor cavity.