초록 ▼

Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hy

Gas turbine engine systems involving hydrostatic face seals with back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a hydrostatic seal having a seal face and a seal runner; and a back-up seal; wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine.

대표청구항 ▼

1. A seal assembly for a gas turbine engine comprising: a hydrostatic seal removably mounted within the gas turbine engine by a mounting bracket, the hydrostatic seal having a seal face and a seal runner, wherein the seal face and the mounting bracket comprise a seal face assembly, and wherein the m

1. A seal assembly for a gas turbine engine comprising: a hydrostatic seal removably mounted within the gas turbine engine by a mounting bracket, the hydrostatic seal having a seal face and a seal runner, wherein the seal face and the mounting bracket comprise a seal face assembly, and wherein the mounting bracket is operative to removably mount the seal face assembly within the gas turbine engine; anda back-up seal spaced at a distance from the hydrostatic seal by an arm, the back-up seal comprising a separate structure from the hydrostatic seal, wherein the back-up seal forms an outlet and the hydrostatic seal forming an inlet of a cavity formed by the mounting bracket and the arm, wherein the back-up seal is labyrinth seal having a land and a knife edge, the knife edge being operative to interact with the land to form a seal, and wherein one of the land and the knife edge is attached to the mounting bracket of the seal face assembly and the other of the land and the knife edge is attached to the mounting bracket of the seal runner assembly;wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine. 2. The assembly of claim 1, 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. 3. The assembly of claim 2, wherein the seal face assembly has a biasing member operative to bias the seal face to the contact position. 4. The assembly of claim 1, wherein at least a portion of the seal face configured to contact the seal runner is formed of a material comprising carbon. 5. A turbine assembly for a gas turbine engine comprising: a hydrostatic seal removably mounted within a turbine of the gas turbine engine by a mounting bracket, the hydrostatic seal having a seal face and a seal runner, wherein the seal face and the mounting bracket comprise a seal face assembly, and wherein the mounting bracket is operative to removably mount the seal face assembly within the gas turbine engine; anda back-up seal spaced at a distance from the hydrostatic seal by an arm, the back-up seal comprising a separate structure from the hydrostatic seal, wherein the back-up seal forms an outlet and the hydrostatic seal forming an inlet of a cavity formed by the mounting bracket and the arm, wherein the back-up seal is labyrinth seal having a land and a knife edge, the knife edge being operative to interact with the land to form a seal, and wherein one of the land and the knife edge is attached to the mounting bracket;wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine. 6. The assembly of claim 5, wherein at least a portion of the seal face configured to contact the seal runner is formed of a material comprising carbon. 7. The assembly of claim 5, wherein the turbine is a low-pressure turbine. 8. The assembly of claim 5, 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. 9. 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 removably mounted within the turbine by a mounting bracket, the hydrostatic seal having a seal face and a seal runner, and the turbine including a back-up seal spaced at a distance from the hydrostatic seal by an arm, wherein the back-up seal comprises a separate structure from the hydrostatic seal, wherein the back-up seal forms an outlet and the hydrostatic seal forming an inlet of a cavity formed by the mounting bracket and the arm, wherein the seal face and the mounting bracket comprise a seal face assembly, and wherein the mounting bracket is operative to removably mount the seal face assembly within the gas turbine engine, and wherein the back-up seal is labyrinth seal having a land and a knife edge, the knife edge being operative to interact with the land to form a seal, and wherein one of the land and the knife edge is attached to the mounting bracket;wherein, in a normal mode of operation of the hydrostatic seal, interaction of the seal face and the seal runner maintains a pressure differential within the gas turbine engine and, in a failure mode of operation of the hydrostatic seal, the back-up seal maintains a pressure differential within the gas turbine engine. 10. The engine of claim 9, wherein at least a portion of the seal face configured to contact the seal runner is formed of a material comprising carbon. 11. The engine of claim 9, wherein the turbine is a low-pressure turbine.