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1. (WO2018128609) SEAL ASSEMBLY BETWEEN A HOT GAS PATH AND A ROTOR DISC CAVITY
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CLAIMS

1. A rotating component (18) of a gas turbine engine (10), comprising: a platform (40) comprising a radially facing endwall (42) and an axial end face

(44),

an airfoil (20) extending radially from the endwall (42),

wherein the end face (44) of the platform (40) faces a seal gap (50) between the rotating component (18) and a stationary component (12) of the gas turbine engine (10), the seal gap (50) being located between a radially outwardly located hot gas path (34) and a radially inwardly located rotor disc cavity (36),

wherein along the end face (44), upstream and downstream positions are defined in relation to a circumferential flow velocity (F) of fluid in the seal gap (50) relative to the end face (44), resultant from rotation of the rotating component (18), wherein the end face (44) is provided with a groove (60), the groove (60) comprising:

a groove floor (62) comprising an inclined portion (62a) having increasing depth along a downstream direction, and

a sidewall (64) located downstream of the groove floor (62) and facing the groove floor (62), the sidewall (64) intersecting the groove floor (62) extending orthogonal to the end face (44),

wherein a radially outer end (68) of the sidewall (64) is circumferentially offset from a radially inner end (66) of the sidewall (64), the radially outer end (68) being located downstream of the radially inner end (66).

2. The rotating component (18) according to claim 1, wherein the sidewall (64) has a curved profile extending from the radially inner end (66) to the radially outer end (68), having a concave face adjacent to the groove floor (62).

3. The rotating component (18) according to claim 1, wherein the sidewall (64) is planar, having a linear profile extending from the radially inner end (66) to the radially outer end (68).

4. The rotating component (18) according to claim 1, wherein the inclined portion (62a) of the groove floor (62) has a decreasing radial width (WR) in an upstream direction.

5. The rotating component (18) according to claim 4, wherein the inclined portion (62a) of the groove floor (62) is triangular shaped.

6. The rotating component (18) according to claim 1, wherein the groove floor (62) further comprises a flat portion (62b) at a constant depth, the flat portion (62b) being located between the inclined portion (62a) of the groove floor (62) and the sidewall (64).

7. The rotating component (18) according to claim 1, wherein the circumferential location of the groove (60) on the end face (44) is near a leading edge (76) of the airfoil (20).

8. The rotating component (18) according to claim 1, wherein the platform (40) is located at a radially inner end of the airfoil (20).

9. The rotating component (18) according to claim 1, wherein the platform (40) is located at a radially inner end of the airfoil (20).

10. A seal assembly (100) between a hot gas path (34) and a rotor disc cavity (36) in a gas turbine engine (10), the seal assembly (100) comprising:

a first seal face (44) formed by an axial end face (44) of a blade platform (40), from which blade platform (40) a plurality of blade airfoils (20) extend radially to form a blade assembly (18),

a second seal face (84) formed by an axial end face (84) of a vane platform (80), from which vane platform (80) a plurality of vane airfoils (14) extend radially to form a vane assembly (12) axially adjacent to the blade assembly (18),

wherein the first (44) and second (84) seal faces face each other with a seal gap (50) defined therebetween, the seal gap (50) being located between a radially outwardly located hot gas path (34) and a radially inwardly located rotor disc cavity (36),

wherein along the first seal face (44), upstream and downstream positions are defined in relation to a circumferential flow velocity (F) of fluid in the seal gap (50) relative to the first seal face (44), resultant from rotation of the blade assembly (18), wherein the first seal face (44) comprises a plurality of circumferential ly spaced grooves (60), each groove (60) comprising:

a groove floor (62) comprising an inclined portion (62a) having increasing depth along a downstream direction, and

a sidewall (64) located downstream of the groove floor (62) and facing the groove floor (62), the sidewall (64) intersecting the groove floor (62) extending orthogonal to the first seal face (44),

wherein a radially outer end (68) of the sidewall (64) is circumferential ly offset from a radially inner end (66)of the sidewall (68), the radially outer end (68) being located downstream of the radially inner end (66).

11. The seal assembly (100) according to claim 10, wherein the sidewall (64) has a curved profile extending from the radially inner end (66) to the radially outer end (68), having a concave face adjacent to the groove floor (62).

12. The seal assembly (100) according to claim 10, wherein the sidewall (64) is planar, having a linear profile extending from the radially inner end (66) to the radially outer end (68).

13. The seal assembly (100) according to claim 10, wherein the inclined portion (62a) of the groove floor (62) has a decreasing radial width (WR) in an upstream direction.

14. The seal assembly (100) according to claim 13, wherein the inclined portion (62a) of the groove floor (62) is triangular shaped.

15. The seal assembly (100) according to claim 10, wherein the groove floor (62) further comprises a flat portion (62b) at a constant depth, the flat portion (62b) being located between the inclined portion (62a) of the groove floor (62) and the sidewall (64).

16. The seal assembly (100) according to claim 10, wherein the circumferential locations of the grooves (60) on the end face (44) of the blade platform (40) are near respective leading edges (76) of the blade airfoils (20).

17. The seal assembly (100) according to claim 10, wherein the blade platform (40) is located at a radially inner end of the blade airfoils (20).

18. The seal assembly (100) according to claim 10, wherein the blade platform (40) is located at a radially inner end of the blade airfoils (20).