Sealing arrangement between turbine shroud segments
A shroud assembly for a turbine engine includes a seal for sealing a gap between a first mate face of a first shroud segment and a second mate face of a circumferentially adjacent second shroud segment. The seal is received in first and second slots formed respectively on the first and second mate faces. The first and second slots extend axially between a leading edge and a trailing edge of the respective shroud segment. The first slot is open at the leading and the trailing edges while the second slot is open at the leading edge and closed at the trailing edge. The seal has axially extending first and second sides which are receivable respectively within the first and second slots. The seal has an axial length substantially equal to tan axial length of the shroud segments and has a cutout on the second side at a trailing edge end of the seal.
1. A shroud for a turbine engine, comprising:
a first shroud segment having a first mate face and a second shroud segment having a second mate face, the first mate face being positioned circumferentially adjacent to the second mate face,
a seal for sealing a gap between the first and second mate faces,
wherein the seal is received, at least in part, in a first slot formed on the first mate face and a second slot formed on the second mate face,
wherein the first and second slots extend axially between a leading edge and a trailing edge of the respective shroud segment, the first slot being open at the leading edge and at the trailing edge, the second slot being open at the leading edge and closed at the trailing edge,
wherein the seal comprises axially extending first and second sides which are receivable respectively within the first slot and the second slot, the seal having an axial length substantially equal to an axial length of the shroud segments and having a cutout on the second side at a trailing edge end of the seal.
2. The shroud according to claim 1 , wherein an axial length of the cutout is equal to or greater than an axial thickness between a trailing edge end of the second slot and the trailing edge of the second shroud segment.
3. The shroud, according to claim 2 , wherein the axial length of the cutout is greater than the axial thickness between the trailing edge end of the second slot and the trailing edge of the second shroud segment by no more than 0.5% of the axial length of the shroud segments.
4. The shroud according to claim 1 , wherein a width of the cutout is 40-60% of a width of the seal.
5. The shroud according to claim 1 , wherein the seal is a riffle seal comprising a first surface facing a hot gas path and a second surface facing away from the hot gas path,
wherein the first surface is smooth and the second surface comprises a plurality of serrations extending in the axial direction.
6. The shroud according to claim 1 , wherein the first mate face comprises a chamfered portion adjacent to the first slot and extending along the axial length of the first shroud segment.
7. The shroud according to claim 1 , wherein the first side and/or second side of the seal are chamfered along an axial extent thereof.
8. The shroud according to claim 1 , wherein the shroud defines a stationary ring segment positioned radially outward of a row of rotor blades.
9. The shroud according to claim 1 , wherein the shroud defines an outer vane shroud attached to a tip end of a row of stationary vanes.
10. The shroud according to claim 1 , wherein the shroud defines an inner vane shroud attached to a hub end of a row of stationary vanes.
11. A method for installing a shroud of a turbine engine, comprising:
aligning a first shroud segment circumferentially adjacent to a second shroud segment such that a first mate face of the first shroud segment faces a second mate face of the second shroud segment, the first and second shroud segments being aligned such that:
an axially extending first slot on the first mate face is open at a leading edge and at a trailing edge of the first shroud segment, and
an axially extending second slot on the second mate face is open at a leading edge and closed at a trailing edge of the second shroud segment, and
inserting a seal into the first and second slots, the seal having axially extending first and second sides that are received within the first and second slots respectively during the installation, the seal having an axial length substantially equal to an axial length of the shroud segments and having a cutout on the second side at a trailing edge end of the seal,
whereby a closed trailing edge end of the second slot engages with a shoulder formed by the cutout on the second side of the seal, to limit axial movement of the seal toward the trailing edge.