CPC F01D 11/001 (2013.01) [F01D 11/025 (2013.01); F01D 11/04 (2013.01); F01D 25/22 (2013.01); F16J 15/40 (2013.01); F16J 15/445 (2013.01); F16J 15/164 (2013.01)] | 15 Claims |
1. A turbine engine defining a radial direction, comprising:
a rotor;
a stator comprising a carrier;
a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment having a seal face forming a fluid bearing with the rotor; and
a seal support assembly comprising a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine,
wherein the pneumatic engagement assembly defines a first pressure chamber and a second pressure chamber located downstream of the first pressure chamber, wherein the pneumatic engagement assembly includes a retraction member positioned within the first pressure chamber moveable between a first position and a second position along a length of the first pressure chamber, and wherein the first pressure chamber defines an air outlet in fluid communication with the second pressure chamber at a location between the first position and the second position.
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