초록 ▼

Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a

Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner.

대표청구항 ▼

1. A hydrostatic seal for a gas turbine engine comprising: a face seal having a seal face;a seal runner, wherein the seal face and the seal runner define a high-pressure side and a lower-pressure side of the hydrostatic seal;a carrier, the face seal being mounted to the carrier such that the carrier

1. A hydrostatic seal for a gas turbine engine comprising: a face seal having a seal face;a seal runner, wherein the seal face and the seal runner define a high-pressure side and a lower-pressure side of the hydrostatic seal;a carrier, the face seal being mounted to the carrier such that the carrier positions the seal face with respect to the seal runner, wherein the face seal has an air bearing supply channel extending from the high-pressure side to a side on which the seal face is located, and wherein the carrier has an orifice aligned with the air bearing supply channel; anda shield attached to the carrier adjacent the orifice, the carrier operative to form a physical barrier that discourages debris travelling on a radially inward trajectory from entering the air bearing supply channel and thereby reduces a potential for debris to foul the hydrostatic seal formed by the seal face and the seal runner. 2. The seal of claim 1, wherein: the seal further comprises a biasing member operative to bias the seal face toward the seal runner; andthe biasing member being located on the lower-pressure side of the seal. 3. The seal of claim 2, wherein the biasing member comprises a spring. 4. The seal of claim 1, wherein: the seal comprises a stator assembly; andthe seal face is mounted to the stator assembly. 5. The seal of claim 1, wherein: the seal comprises a rotor assembly; andthe seal runner is mounted to the rotor assembly. 6. The seal of claim 1, wherein the air bearing supply channel exhibits a straight configuration. 7. The seal of claim 6, wherein the air bearing supply channel exhibits a non-uniform diameter along a length thereof. 8. A turbine assembly for a gas turbine engine comprising: a turbine having a hydrostatic seal;the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member;the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal, wherein the seal face is a surface of a face seal, the face seal having an air bearing supply channel extending from the high-pressure side to a side on which the seal face is located;the carrier being operative to position the seal face relative to the seal runner;a shield extending outwardly from the carrier on the high-pressure side of the seal, the shield being operative to discourage debris from entering the air bearing supply channel; andthe biasing member being located on the lower-pressure side of the hydrostatic seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the hydrostatic seal causes the carrier to position the seal face relative to the seal runner. 9. The assembly of claim 8, wherein the air bearing supply channel exhibits a straight configuration. 10. The assembly of claim 8, wherein the turbine is a low-pressure turbine. 11. The assembly of claim 8, wherein the hydrostatic seal is provided by a stator assembly and a rotor assembly, at least one of which is removably mountable within the turbine. 12. The assembly of claim 8, wherein the hydrostatic seal is a lift-off seal, with the seal face being biased to a contact position in which the seal face contacts the seal runner. 13. The assembly of claim 8, wherein the air bearing supply channel exhibits a non-uniform diameter along a length thereof. 14. The assembly of claim 8, wherein the carrier has an orifice aligned with the air bearing supply channel. 15. A gas turbine engine comprising: a compressor;a shaft interconnected with the compressor; anda turbine operative to drive the shaft, the turbine having a hydrostatic seal;the hydrostatic seal having a seal face, a seal runner, a carrier and a biasing member;the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal, wherein the seal face is a surface of a face seal, the face seal having an air bearing supply channel extending from the high-pressure side to a side on which the seal face is located;the carrier being operative to position the seal face relative to the seal runner;a shield extending outwardly from the carrier on the high-pressure side of the seal, the shield being operative to discourage debris from entering the air bearing supply channel; andthe biasing member being located on the lower-pressure side of the hydrostatic seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the hydrostatic seal causes the carrier to position the seal face relative to the seal runner. 16. The engine of claim 15, wherein at least a portion of the seal face configured to contact the seal runner is formed of a material comprising carbon. 17. The engine of claim 15, wherein the engine is a turbofan. 18. The engine of claim 15, wherein the turbine is a low-pressure turbine. 19. The engine of claim 15, wherein the air bearing supply channel exhibits a straight configuration. 20. The engine of claim 15, wherein the air bearing supply channel exhibits a non-uniform diameter along a length thereof.