Gas turbine engine forward bearing compartment architecture
A turbofan gas turbine engine includes a front center body case structure. A geared architecture is at least partially supported by the front center body case structure. A bearing structure rotationally support a fan shaft. A fan rotor bearing support structure extends radially inward from the front center body and at least partially supports the bearing structure. The fan rotor bearing support structure includes a passage that communicates buffer supply air from a hollow strut to the bearing structure.
1. A turbofan gas turbine engine comprising:
a fan and an outer housing surrounding the fan to define a bypass duct, the fan including a fan rotor;
a first shaft and a second shaft, wherein the first shaft and the second shaft are concentric and are rotatable about an engine central longitudinal axis;
a compressor section including a first compressor and a second compressor axially aft of the first compressor;
a turbine section including a first turbine and a fan drive turbine, the first shaft driven by the fan drive turbine, and the second shaft interconnecting the second compressor and the first turbine;
a front center body case structure defining a first core flow path for core airflow into the first compressor, and the front center body case structure including a hollow strut spanning across the first core flow path;
a geared architecture at least partially supported by the front center body case structure, and wherein the fan drive turbine drives the geared architecture to drive the fan rotor at a speed lower than a speed of the fan drive turbine;
a first bearing structure forward of the geared architecture relative to the engine central longitudinal axis, the first bearing structure rotationally supporting a fan shaft, and the fan shaft interconnecting the fan rotor and an output of the geared architecture; and
a fan rotor bearing support structure extending radially inward from the front center body case structure relative to the engine central longitudinal axis, the fan rotor bearing support structure at least partially supporting the first bearing structure, and the fan rotor bearing support structure including a passage that communicates buffer supply air from the hollow strut to the first bearing structure.
2. The turbofan gas turbine engine as recited in claim 1 , wherein the geared architecture is an epicyclic transmission.
3. The turbofan gas turbine engine as recited in claim 2 , further comprising:
a flex support that provides a flexible attachment of the geared architecture within the front center body case structure.
4. The turbofan gas turbine engine as recited in claim 2 , wherein each of the first compressor, the second compressor, the first turbine and the fan drive turbine includes a plurality of stages.
5. The turbofan gas turbine engine as recited in claim 4 , further comprising:
an intermediate case structure defining a second core flow path for core airflow into the second compressor, the intermediate case structure mounted to an aft end of the front center body case structure.
6. The turbofan gas turbine engine as recited in claim 5 , wherein the first compressor includes three stages, and the fan drive turbine includes a greater number of stages than the first compressor.
7. The turbofan gas turbine engine as recited in claim 6 , further comprising:
a flex support that provides a flexible attachment of the geared architecture within the front center body case structure; and
a coupling shaft that interconnects the first shaft and an input of the geared architecture and that facilitates the segregation of vibrations.
8. The turbofan gas turbine engine as recited in claim 6 , wherein the first bearing structure is axially forward of the hollow strut relative to the engine central longitudinal axis.
9. The turbofan gas turbine engine as recited in claim 8 , wherein the fan drive turbine drives both the geared architecture and the first compressor.
10. The turbofan gas turbine engine as recited in claim 9 , wherein the first bearing structure is located within a first bearing compartment, the first bearing compartment is isolated by the geared architecture from a second bearing compartment, a second bearing is located within the second bearing compartment at a position axially aft of the geared architecture with respect to the engine central longitudinal axis, and the front center body case structure defines the second bearing compartment.
11. The turbofan gas turbine engine as recited in claim 10 , wherein the first bearing compartment operates as a thermal ground with respect to the buffer supply air communicated the fan rotor bearing support structure.
12. The turbofan gas turbine engine as recited in claim 11 , wherein the first compressor includes a tubular hub and a frustro-conical web that supports a plurality of airfoils, and the tubular hub mounts to the first shaft.
13. The turbofan gas turbine engine as recited in claim 12 , wherein the frustro-conical web extends in a forwardly direction from the tubular hub at a position axially between the second bearing structure and a third bearing structure relative to the engine central longitudinal axis, the second bearing structure supports the first shaft, and the third bearing structure supports the second shaft.
14. The turbofan gas turbine engine as recited in claim 10 , wherein the first bearing structure includes a first bearing and a second bearing.
15. The turbofan gas turbine engine as recited in claim 14 , wherein the buffer supply air is communicated from the compressor section to the hollow strut.
16. The turbofan gas turbine engine as recited in claim 15 , wherein the passage in the fan rotor bearing support structure slopes in a forwardly direction from the hollow strut to the first bearing structure relative to the engine central longitudinal axis.
17. The turbofan gas turbine engine as recited in claim 16 , wherein the hollow strut is axially aft of a vane in the first core flow path relative to the engine central longitudinal axis.
18. The turbofan gas turbine engine as recited in claim 17 , wherein the buffer supply air is communicated from the first bearing structure to the first core flow path.
19. The turbofan gas turbine engine as recited in claim 10 , wherein the epicyclic transmission is a planetary gear system.
20. The turbofan gas turbine engine as recited in claim 19 , further comprising:
a conditioning device that communicates the buffer supply air to the hollow strut.
21. The turbofan gas turbine engine as recited in claim 20 , wherein the conditioning device is a heat exchanger.
22. The turbofan gas turbine engine as recited in claim 21 , wherein the conditioning device interconnects the hollow strut and the second compressor.
23. The turbofan gas turbine engine as recited in claim 22 , further comprising:
a valve that selects between first and second bleed flows from the second compressor.
24. The turbofan gas turbine engine as recited in claim 23 , wherein the valve is coupled to a control.
25. The turbofan gas turbine engine as recited in claim 10 , wherein the epicyclic transmission is a star gear system.
26. The turbofan gas turbine engine as recited in claim 25 , further comprising:
a conditioning device that communicates the buffer supply air to the hollow strut.
27. The turbofan gas turbine engine as recited in claim 26 , wherein the conditioning device is a heat exchanger.
28. The turbofan gas turbine engine as recited in claim 27 , wherein the conditioning device interconnects the hollow strut and the second compressor.
29. The turbofan gas turbine engine as recited in claim 28 , further comprising:
a valve that selects between first and second bleed flows from the second compressor.
30. The turbofan gas turbine engine as recited in claim 29 , wherein the valve is coupled to a control.