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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 turbin

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.

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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

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, anda 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. 2. The outer rim seal arrangement of claim 1, wherein the guide vanes impart swirl about the rotor disc longitudinal axis to a flow of cooling fluid flowing from the rotor cavity and into the outer cavity. 3. The outer rim seal arrangement of claim 1, further comprising pumping fins disposed on the upper angel wing seal aft end in the upper angel wing seal gap and configured to encourage a flow of cooling fluid from the outer cavity and into the hot gas path. 4. The outer rim seal arrangement of claim 3, further comprising a discourager tooth disposed on the rim fore-end and in the upper angel wing seal gap, the discourager tooth effective to discourage flow from the hot gas path and into the outer cavity. 5. The outer rim seal arrangement of claim 1, further comprising a discourager tooth disposed on the rim fore-end in the upper angel wing seal gap, the discourager tooth effective to discourage flow from the hot gas path and into the outer cavity. 6. An outer rim seal arrangement for a gas turbine engine, comprising: a last stage turbine blade disposed on a rotor disc, in a hot gas path, downstream of other turbine blades, and comprising an internal cooling passage;an annular and stationary rim centered about a longitudinal axis of the rotor disc comprising a fore-end adjacent an aft side of a base of the turbine blade, an radially outward-facing surface, and an radially inward-facing surface;a lower angel wing extending aft from the turbine blade base and comprising an aft end disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap between an outer cavity and a rotor cavity;an upper angel wing extending aft from the turbine blade base and comprising an aft end disposed radially outward of the rim outward-facing surface to define an upper angel wing seal gap between the hot gas path and the outer cavity;flow guiding elements in at least one of the lower angel wing seal gap and the upper angel wing seal gap effective to preventingestion of hot gas into the outer cavity or the rotor cavity, andan air supply passage providing fluid communication between the rotor cavity and a source of a cooling fluid at atmospheric pressure,wherein when the blade is rotating during operation the rotation reduces a static pressure in the rotor cavity to below the atmospheric pressure, effective to draw the cooling fluid through the air supply passage. 7. The outer rim seal arrangement of claim 6, wherein the flow guiding elements comprise guide vanes disposed on the rim inward-facing surface in the lower angel wing seal gap, wherein the guide vanes impart swirl about the rotor disc longitudinal axis to a flow of cooling fluid flowing from the rotor cavity and into the outer cavity. 8. The outer rim seal arrangement of claim 6, wherein the flow guiding elements comprise pumping fins disposed on the upper angel wing seal aft end in the upper angel wing seal gap and configured to encourage a flow of cooling fluid from the outer cavity and into the hot gas path. 9. The outer rim seal arrangement of claim 6, further comprising a discourager tooth disposed on the rim fore-end and in the upper angel wing seal gap. 10. The outer rim seal arrangement of claim 6, wherein the flow guiding elements comprise: guide vanes disposed on the rim inward-facing surface in the lower angel wing seal gap, wherein the guide vanes impart swirl about the rotor disc longitudinal axis to a flow of cooling fluid flowing from the rotor cavity and into the outer cavity; andpumping fins disposed on the upper angel wing seal aft end in the upper angel wing seal gap and configured to encourage a flow of cooling fluid from the outer cavity and into the hot gas path, andwherein the outer rim seal arrangement further comprises a discourager tooth disposed on the rim fore-end and in the upper angel wing seal gap. 11. An outer rim seal arrangement for a gas turbine engine, comprising: a turbine blade disposed on a rotor disc, in a hot gas path, and comprising an internal cooling passage, wherein when rotating during operation the rotation is effective to motivate a cooling fluid through the internal cooling passage;a first cooling fluid path external to the turbine blade and from a rotor cavity, the first cooling path extending through a lower angel wing seal gap on an aft side of the turbine blade, an outer cavity, an upper angel wing seal gap on the aft side of the turbine blade, and leading to the hot gas path;a second cooling fluid path from the rotor cavity, said second cooling path extending through a portion of the internal cooling passage, into the outer cavity, through the upper angel wing seal gap, and leading to the hot gas path;an air supply passage providing fluid communication between the rotor cavity and a source of the cooling fluid at atmospheric pressure; anda flow guiding element in at least one of the lower angel wing seal gap and the upper angel wing seal gap effective to discourage ingestion of hot gas from the hot gas path,wherein when the blade is rotating during operation the rotation reduces a static pressure in the rotor cavity to below the atmospheric pressure, effective to draw the cooling fluid through the air supply passage. 12. The outer rim seal arrangement of claim 11, wherein the flow guiding element comprises pumping fins disposed on an upper angel wing seal aft end in the upper angel wing seal gap and configured to encourage a flow of cooling fluid in the first cooling fluid path flow and a flow of cooling fluid in the second cooling fluid path. 13. The outer rim seal arrangement of claim 11, wherein the flow guiding element comprises guide vanes disposed on a stationary rim radially inward-facing surface in the lower angel wing seal gap, wherein the guide vanes impart swirl about a longitudinal axis of the rotor disc to a flow of cooling fluid flowing from the rotor cavity and into the outer cavity. 14. The outer rim seal arrangement of claim 13, wherein the guide vanes are oriented to present a convex side of the guide vane across a flow direction of ingested gases. 15. The outer rim seal arrangement of claim 11, wherein the flow guiding element comprises a discourager tooth disposed on a stationary rim fore-end and in the upper angel wing seal gap. 16. The outer rim seal arrangement of claim 11, wherein the flow guiding element comprises: pumping fins disposed on an upper angel wing seal aft end in the upper angel wing seal gap and configured to encourage a flow of cooling fluid in the first cooling fluid path and a flow of cooling fluid in the second cooling fluid path;guide vanes disposed on a stationary rim radially inward-facing surface in the lower angel wing seal gap, wherein the guide vanes impart swirl about a longitudinal axis of the rotor disc to a flow of cooling fluid flowing from the rotor cavity and into the outer cavity; anda discourager tooth disposed on a stationary rim fore-end and in the upper angel wing seal gap. 17. The outer rim seal arrangement of claim 1, wherein the blade is a last stage blade of a series of blades in a turbine. 18. The outer rim seal arrangement of claim 11, further comprising a preswirler disposed between the air supply passage and the rotor cavity. 19. The outer rim seal arrangement of claim 11, wherein the blade is a last stage blade in a series of blades in a turbine. 20. The outer rim seal arrangement of claim 11, further comprising a preswirler disposed downstream of the blade, between the air supply passage and the rotor cavity.