GAS TURBINE ENGINE NON-ROTATING STRUCTURE WEDGE SEAL
A seal assembly arrangement for a gas turbine engine includes first and second non-rotating structures respectively that provide first and second faces. A sealing assembly includes first and second sealing rings respectively that engage the first and second faces. The first and second sealing rings slideably engage one another at a sliding wedge interface.
1 . A seal assembly arrangement for a gas turbine engine comprising:
first and second non-rotating structures respectively providing first and second faces;
a sealing assembly includes first and second sealing rings respectively engaging the first and second faces, the first and second sealing rings slideably engaging one another at a sliding wedge interface.
2 . The seal assembly arrangement according to claim 1 , wherein the seal assembly separates first and second pressurized areas from one another, one of the first and second pressurized areas corresponding to a core flow path.
3 . The seal assembly arrangement according to claim 2 , wherein the first non-rotating structure is a blade outer air seal and the second non-rotating structure is a stator vane.
4 . The seal assembly arrangement according to claim 3 , wherein the stator vane is arranged in a turbine section.
5 . The seal assembly arrangement according to claim 3 , wherein a pocket is provided in at least one of the stator vane and the blade outer air seal, the sealing assembly arranged in the pocket.
6 . The seal assembly arrangement according to claim 5 , wherein the pocket is provided in an outer platform of the stator vane.
7 . The seal assembly arrangement according to claim 1 , wherein a pocket is provided in at least one of the first and second non-rotating structures, the sealing assembly arranged in the pocket.
8 . The seal assembly arrangement according to claim 1 , wherein at least one of the first and second sealing rings includes free and compressed conditions corresponding to uninstalled and installed conditions, the at least one sealing ring having free ends spaced apart from another in the compressed condition.
9 . The seal assembly arrangement according to claim 8 , wherein one of the free ends includes a protrusion and the other of the free ends includes a slot receiving the protrusion.
10 . The seal assembly arrangement according to claim 1 , wherein the first and second sealing rings are constructed from a metal alloy.
11 . The seal assembly arrangement according to claim 10 , wherein at least one surface of at least one of the first and second sealing rings includes a hard coat.
12 . The seal assembly arrangement according to claim 10 , wherein at least one surface of at least one of the first and second sealing rings includes a lubrication coating.
13 . The seal assembly arrangement according to claim 10 , wherein a surface of at least one of the first and second sealing rings includes a ridge engaging the other of the first and second sealing rings.
14 . The seal assembly arrangement according to claim 13 , wherein another surface of the other of the first and second sealing rings includes another ridge that engages the surface of the at least one of the first and second sealing rings.
15 . The seal assembly arrangement according to claim 1 , wherein the sliding wedge interface is provided by first and second angled surfaces respectively provided by the first and second sealing rings, the first and second angled surfaces canted relative to an axis of the first and second sealing rings.
16 . A method of sealing between two gas turbine engine components, comprising the steps of:
arranging first and second sealing rings between first and second non-rotating structures; and
biasing the first and second sealing rings into engagement with one another at a sliding wedge interface and into engagement with the first and second non-rotating structures.
17 . The method according to claim 16 , wherein the seal assembly separates first and second pressurized areas from one another, one of the first and second pressurized areas corresponding to a core flow path.
18 . The method according to claim 17 , wherein the first non-rotating structure is a blade outer air seal and the second non-rotating structure is a stator vane.
19 . The method according to claim 18 , wherein the stator vane is arranged in a turbine section.
20 . The method according to claim 18 , wherein a pocket is provided in at least one of the stator vane and the blade outer air seal, the sealing assembly arranged in the pocket.