Housing less front bearing compartment for gas turbine engine
A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.
1. A fan assembly of a gas turbine engine, comprising:
a fan rotor including:
a fan rotor hub; and
a plurality of fan blades extending radially outwardly from the fan rotor hub;
a fan case including:
an inner case portion;
an outer case portion surrounding the plurality of fan blades; and
a plurality of struts extending between the inner case portion and the outer case portion;
a bearing assembly configured to support the fan rotor at the inner case portion, the bearing assembly including:
a bearing inner race secured to the fan rotor;
a bearing outer race secured to the inner case portion; and
a plurality of bearing elements located radially between the bearing inner race and the bearing outer race; and
an oil return feature located at a first strut of the plurality of struts, configured to collect used lubricant and direct the used lubricant away from the bearing assembly;
wherein the oil return feature includes a plurality of oil return ports extending through the first strut wherein a first oil return port of the plurality of oil return ports is located axially forward of the plurality of bearing elements, and at least a second oil return port of the plurality of oil return ports is located axially aft of the plurality of bearing elements.
2. The fan assembly of claim 1 , wherein the bearing outer race is secured to a radially inner surface of the inner case portion of the fan case.
3. The fan assembly of claim 1 , further comprising an oil supply tube extending through a first second strut of the plurality of struts, the oil supply tube including an oil jet nozzle to direct lubricant onto the bearing assembly.
4. The fan assembly of claim 3 , wherein the oil jet nozzle is located aftward of the plurality of bearing elements.
5. The fan assembly of claim 3 , wherein the first second strut is a vertically topmost strut of the plurality of struts.
6. The fan assembly of claim 1 , wherein the first oil return port has a smaller cross-sectional area than the second oil return port.
7. The fan assembly of claim 1 , further comprising at least one sealing structure to prevent contamination entry into and oil leakage from the bearing assembly.
8. A gas turbine engine, comprising:
a combustor;
a turbine driven by combustion gases output from the combustor; and
a fan assembly, including:
a fan rotor driven by the turbine including:
a fan rotor hub; and
a plurality of fan blades extending radially outwardly from the fan rotor hub;
a fan case including:
an inner case portion;
an outer case portion surrounding the plurality of fan blades;
a plurality of struts extending between the inner case portion and the outer case portion;
a bearing assembly configured to support the fan rotor at the inner case portion, the bearing assembly including:
a bearing inner race secured to the fan rotor
a bearing outer race secured to the inner case portion; and
a plurality of bearing elements located radially between the bearing inner race and the bearing outer race; and
an oil return feature located at a first strut of the plurality of struts, configured to collect used lubricant and direct the used lubricant away from the bearing assembly;
wherein the oil return feature includes a plurality of oil return ports extending through the first strut wherein a first oil return port of the plurality of oil return ports is located axially forward of the plurality of bearing elements, and at least a second oil return port of the plurality of oil return ports is located axially aft of the plurality of bearing elements.
9. The gas turbine engine of claim 8 , wherein the bearing outer race is secured to a radially inner surface of the inner case portion of the fan case.
10. The gas turbine engine of claim 8 , further comprising an oil supply tube extending through a first second strut of the plurality of struts, the oil supply tube including an oil jet nozzle to direct lubricant onto the bearing assembly from a radially outward side of the bearing assembly.
11. The gas turbine engine of claim 10 , wherein the oil jet nozzle is located aftward of the plurality of bearing elements.
12. The gas turbine engine of claim 10 , wherein the second strut is a vertically topmost strut of the plurality of struts.
13. The gas turbine engine of claim 8 , wherein the first oil return port has a smaller cross-sectional area than the second oil return port.
14. The gas turbine engine of claim 8 , further comprising at least one sealing structure to prevent contamination entry into and oil leakage from the bearing assembly.