Managing spool bearing load using variable area flow nozzle
A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.
1. A turbine engine comprising:
a bearing, and a sensor in communication with the bearing and configured to detect a load condition;
a fan nacelle including a nozzle exit area;
a flow control device adapted to effectively change the nozzle exit area; and
a controller in communication with the sensor and configured to command the flow control device in response to an undesired load on the bearing to adjust the fan nozzle exit area.
2. The turbine engine according to claim 1 , wherein the bearing supports a spool having a turbine, and the nacelle is a core nacelle surrounding the turbine, and a fan is arranged upstream from the core nacelle and coupled to the spool, the fan nacelle surrounding the fan and core nacelle and providing a bypass flow path that includes the nozzle exit area.
3. A turbine engine comprising:
a bearing;
a nacelle including a nozzle exit area;
a flow control device adapted to effectively change the nozzle exit area;
a controller programmed to monitor the bearing and command the flow control device in response to an undesired load on the bearing; and
wherein the bearing supports a spool having a turbine, and the nacelle is a core nacelle surrounding the turbine, and a fan is arranged upstream from the core nacelle and coupled to the spool, the fan nacelle surrounding the fan and core nacelle and providing a bypass flow path that includes the nozzle exit area, wherein the spool is a low pressure spool, and the turbine is a low pressure turbine.
4. The turbine engine according to claim 3 , wherein the low pressure spool includes first and second portions, the first portion supporting the low pressure turbine and the second portion supporting the fan, and a gear train interconnecting the first and second portions of the low pressure spool.
5. The turbine engine according to claim 3 , wherein the low pressure spool supports a low pressure compressor, and a high pressure spool coaxial with the low pressure spool and supporting a high pressure turbine.
6. The turbine engine according to claim 1 , wherein the flow control device includes a member moveable between open and closed positions to physically change the nozzle exit area.
7. The turbine engine according to claim 1 , wherein the flow control device includes an actuator for manipulating a member to effectively change the nozzle exit area.
8. The turbine engine according to claim 2 , wherein the bearing is a thrust bearing and the undesired load is an undesired thrust load along an axis provided by the spool.
9. The turbine engine according to claim 1 , wherein the controller is programmed to acquire load data, and a memory adapted to store the load data.