Air seal system with backside abradable layer
A seal system for a gas turbine engine includes a ceramic matrix composite (CMC) seal arc segment and a carrier supporting the CMC seal arc segment. The CMC seal arc segment defines radially inner and outer sides and has an abradable layer disposed on the radially outer side. There is a cooling cavity radially between the carrier and the abradable layer. The carrier includes a ridge that projects into a groove in the abradable layer and provides a labyrinth seal that partitions the cooling cavity into sub-cavities.
1. A seal system for a gas turbine engine comprising:
a ceramic matrix composite (CMC) seal arc segment defining radially inner and outer sides and having an abradable layer disposed on the radially outer side;
a carrier supporting the CMC seal arc segment;
a cooling cavity radially between the carrier and the abradable layer; and
the carrier including a ridge projecting into a groove in the abradable layer and thereby providing a labyrinth seal that partitions the cooling cavity into sub-cavities, the ridge having a knife edge.
2. The seal system as recited in claim 1 , wherein the abradable layer is selected from the group consisting of pure silicon, yttria stabilized zirconia, gadolinia stabilized zirconia, and combinations thereof.
3. The seal system as recited in claim 1 , wherein the carrier includes radially inner and outer carrier sides, the radially inner carrier side bounds the sub-cavities, the carrier includes a first supply passage that opens at the radially outer carrier side and at the radially inner carrier side to one of the sub-cavities, and the carrier includes a second supply passage that opens at the radially outer carrier side and at the radially inner carrier side to another, different one of the sub-cavities.
4. The seal system as recited in claim 3 , wherein the outer side of the CMC arc segment has a pair of hooks that define a dovetail slot there between, the carrier has a dovetail disposed in the dovetail slot, and the first supply passage and the second supply passage are through the dovetail.
5. The seal system as recited in claim 4 , wherein the CMC seal arc segment defines forward and aft sides, one of the hooks of the pair of hooks is elongated along the forward side, and the other of the hooks of the pair of hooks is elongated along the aft side.
6. The seal system as recited in claim 1 , wherein the sub-cavities are pressurized at different pressures.
7. The seal system as recited in claim 1 , wherein the carrier, including the ridge, is selected from the group consisting of a Ni-based alloy and a cobalt-based alloy.
8. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section having a seal system disposed about a central axis of the gas turbine engine, the seal system including:
a ceramic matrix composite (CMC) seal arc segment defining radially inner and outer sides and having an abradable layer disposed on the radially outer side; and
a carrier supporting the CMC seal arc segment;
a cooling cavity radially between the carrier and the abradable layer; and
the carrier including a ridge projecting into a groove in the abradable layer and thereby providing a labyrinth seal that partitions the cooling cavity into sub-cavities, the ridge having a knife edge.
9. The gas turbine engine as recited in claim 8 , wherein the carrier includes radially inner and outer carrier sides, the radially inner carrier side bounds the sub-cavities, the carrier includes a first supply passage that opens at the radially outer carrier side and at the radially inner carrier side to one of the sub-cavities, the carrier includes a second supply passage that opens at the radially outer carrier side and at the radially inner carrier side to another, different one of the sub-cavities, the outer side of the CMC arc segment has a pair of hooks that define a dovetail slot there between, the carrier has a dovetail disposed in the dovetail slot, and the first supply passage and the second supply passage are through the dovetail.
10. The gas turbine engine as recited in claim 8 , wherein the sub-cavities are pressurized at different pressures.
11. The gas turbine engine as recited in claim 10 , wherein the abradable layer is selected from the group consisting of pure silicon, yttria stabilized zirconia, gadolinia stabilized zirconia, and combinations thereof, and the carrier, including the ridge, is selected from the group consisting of a Ni-based alloy and a cobalt-based alloy.