Buffer air method and system for a bearing compartment
A method of operation is provided during which buffer air flows into a buffer cavity in a turbine engine. The buffer cavity surrounds a bearing compartment in the turbine engine. Leakage air flows across a buffer seal device in the turbine engine. The buffer air and the leakage air are combined to provide combined air. The combined air is vented to a pressure sink such that: a pressure of the buffer air within the buffer cavity is maintained at or below a maximum buffer air threshold during operation of the turbine engine; and a flowrate of the leakage air across the buffer seal device is maintained at or above a minimum leakage air threshold during the operation of the turbine engine.
1. A method of operation, comprising:
flowing buffer air into a buffer cavity in a turbine engine, the buffer cavity surrounding a bearing compartment in the turbine engine;
flowing leakage air across a buffer seal device in the turbine engine;
combining the buffer air and the leakage air to provide combined air; and
venting the combined air to a pressure sink such that
a pressure of the buffer air within the buffer cavity is maintained at or below a maximum buffer air threshold during operation of the turbine engine; and
a flowrate of the leakage air across the buffer seal device is maintained at or above a minimum leakage air threshold during the operation of the turbine engine.
2. The method of claim 1 , wherein the combined air is vented to the pressure sink through a valve.
3. The method of claim 2 , wherein the valve is configured as a discrete position valve.
4. The method of claim 2 , wherein the valve is configured as a variable position valve.
5. The method of claim 2 , further comprising controlling operation of the valve using an electronic control system for the turbine engine.
6. The method of claim 2 , further comprising:
monitoring an operational parameter of the turbine engine; and
controlling operation of the valve based on the operational parameter.
7. The method of claim 1 , wherein at least some of the combined air is vented to the pressure sink throughout the operation of the turbine engine.
8. The method of claim 1 , wherein
the leakage air flows across the buffer seal device from a high pressure cavity in the turbine engine to a low pressure cavity in the turbine engine;
the buffer air is combined with the leakage air in the low pressure cavity;
the low pressure cavity surrounds the buffer cavity; and
the high pressure cavity surrounds the low pressure cavity.
9. The method of claim 8 , wherein
a low pressure cavity wall in the turbine engine includes a sidewall and an endwall;
the sidewall is radially between and forms the low pressure cavity and the high pressure cavity;
the endwall projects radially inward from the sidewall, and the endwall is axially between and forms the low pressure cavity and the high pressure cavity; and
the buffer seal device seals a gap between the endwall and a rotating structure in the turbine engine.
10. The method of claim 8 , wherein at least one of
the buffer cavity is radially adjacent the bearing compartment;
the low pressure cavity is radially adjacent the buffer cavity; or
the high pressure cavity is radially adjacent the low pressure cavity.
11. The method of claim 8 , wherein at least one of
the buffer cavity axially overlaps the bearing compartment;
the low pressure cavity axially overlaps the buffer cavity; or
the high pressure cavity axially overlaps the low pressure cavity.
12. The method of claim 8 , wherein
a diffuser plenum in the turbine engine surrounds the high pressure cavity; and
a combustor in the turbine engine is disposed within the diffuser plenum.
13. The method of claim 8 , wherein the high pressure cavity is radially inboard of a core flowpath within the turbine engine.
14. The method of claim 1 , wherein a bearing compartment wall in the turbine engine includes
a sidewall radially between and forming the bearing compartment and the buffer cavity;
a first endwall projecting radially inward from the sidewall, the first endwall axially between and forming the bearing compartment and the buffer cavity; and
a second endwall projecting radially inward from the sidewall, the second endwall axially between and forming the bearing compartment and the buffer cavity.
15. The method of claim 1 , wherein
a bearing compartment wall in the turbine engine is disposed between and forms the bearing compartment and the buffer cavity;
each of a plurality of bearing seal devices in the turbine engine seal a respective gap between the bearing compartment wall and a rotating structure in the turbine engine; and
the bearing compartment is disposed axially between the plurality of bearing seal devices.
16. The method of claim 1 , wherein both the buffer cavity and the bearing compartment are formed by a stationary structure and a rotating structure in the turbine engine.
17. An assembly for a turbine engine, comprising:
a stationary structure forming a bearing compartment, a buffer cavity, a low pressure cavity and a high pressure cavity, the buffer cavity outboard of the bearing compartment, the low pressure cavity outboard of the buffer cavity, and the high pressure cavity outboard of the low pressure cavity;
a vent line fluidly coupled with the low pressure cavity, the low pressure cavity configured to direct leakage air from the high pressure cavity and buffer air from the buffer cavity into the vent line as low pressure air;
a valve fluidly coupled with and downstream of the vent line; and
a control system configured to signal the valve to control venting of the low pressure air from the low pressure cavity through the vent line such that
a pressure of the buffer air within the buffer cavity is maintained at or below a maximum buffer air threshold; and
a flowrate of the leakage air across the buffer seal device is maintained at or above a minimum leakage air threshold.
18. The assembly of claim 17 , wherein the valve is configured as one of a two-position valve and a variable position valve.