Patent ID: 11913340
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  B  Y | IPC F

Claim 7:
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.