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 e
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.
대표청구항▼
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; anda vane,wherein the ring is coupled to the vane,wherein the vane includes a plurality of segm
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; anda 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, andwherein 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; anda 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, andwherein 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.
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이 특허에 인용된 특허 (16)
Bosna Alexander A. (135 Summit Rd. Malvern PA 19355) Riccio Louis M. (161 Hollow Rd. Malvern PA 19355), Abradable non-metallic seal for rotating turbine engine.
Stevens Leonard W. (Vernon CT) Siwik William S. (Manchester CT) Moore William A. (Durham CT) Brown Wayne M. (North Granby CT) Barnard Andrew A. (Glastonbury CT), Bearing compartment protection system.
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