Turbine cavity sealing assembly
Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting HALO seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane.
1. A gas turbine engine, comprising:
a sealing assembly that includes:
a non-contacting seal;
a ring constructed as a full ring that carries the seal;
a rotatable sealing land that interfaces with the seal; and
a vane,
wherein the ring is coupled to the vane,
wherein the vane includes a plurality of segments, and wherein vane segments that are within a radially inner diameter cavity are at least one of feathersealed or shiplapped in order to form a cooling air plenum to store at least some of a cooling pressure,
wherein the cooling air plenum includes a connection on the vane that is coupled to a tube on the ring, and
wherein the tube includes at least one of a sliding joint or a bellow that allows the ring and the vane to expand and contract independent of one another.
2. The engine of claim 1 , wherein the ring is coupled to the vane using at least four centering features.
3. The engine of claim 2 , wherein each of the at least four centering features includes at least one slot formed in the ring, and wherein at least one attachment mechanism includes at least one of: a pin, a clip, a fastener, or some other local feature to mate with the slot and center the ring.
4. The engine of claim 1 , further comprising:
a rotor structure associated with a turbine blade located forward of the seal, the ring, and the sealing land,
wherein the rotor structure, the ring, and the sealing land at least partially define a first cavity.
5. The engine of claim 4 , wherein the ring and the vane form a subdivided part of the first cavity by subdividing the first cavity into a radially outer region and a radially inner region, wherein the radially inner region serves as a first source of cool air for the radially outer region.
6. The engine of claim 5 , further comprising:
a compressor section configured to provide a second source of cool air to the first cavity.
7. The engine of claim 6 , wherein the rotor structure is associated with a third source of cool air that is configured to be provided to the first cavity.
8. The engine of claim 4 , further comprising:
a first side plate coupled to the rotor structure.
9. The engine of claim 8 , further comprising:
a second rotor structure associated with a second turbine blade located aft of the seal, the ring, and the sealing land,
wherein the second rotor structure, the ring, and the sealing land at least partially define a second cavity.
10. The engine of claim 9 , further comprising:
a second side plate coupled to the second rotor structure.
11. The engine of claim 1 , wherein the tube is welded into the ring.
12. A gas turbine engine, comprising:
a sealing assembly that includes:
a non-contacting seal;
a ring that carries the seal;
a rotatable sealing land that interfaces with the seal; and
a vane,
wherein the ring is coupled to the vane,
wherein the vane includes segments that are within a radially inner diameter cavity and are at least one of feathersealed or shiplapped in order to form a cooling air plenum,
wherein the cooling air plenum includes a connection on the vane that is coupled to a tube on the ring, and
wherein the tube includes at least one of a sliding joint or a bellow that allows the ring and the vane to expand and contract independent of one another.