Flanged integral piston bearing

1. A method of operating a gas turbine engine of a multi-engine aircraft, the gas turbine engine having an engine shaft mounted for rotation in a bearing of a bearing assembly, the method comprising:

limiting motive power supplied to the aircraft by the gas turbine engine by operating the gas turbine engine in a standby mode; and

at least when the gas turbine engine is operating in the standby mode, using an oil piston integrated in the bearing supporting the engine shaft of the gas turbine engine to generate an axial preload force on the bearing.

2. The method as defined in claim 1 , further comprising operating another gas turbine engine of the multi-engine aircraft in an active mode to supply a larger amount of motive power to the aircraft than the gas turbine engine operated in the standby mode.

3. The method as defined in claim 2 , wherein the gas turbine engines drive a common load, wherein operating one of the gas turbine engine in the standby mode supplies none of a required motive power to the common load, while the gas turbine engine in the active mode supplies all of the required motive power to the common load.

4. The method as defined in claim 1 , wherein using the oil piston includes supplying pressurized oil into a piston cavity of the bearing assembly from an oil supply of the gas turbine engine.

5. The method as defined in claim 1 , the oil piston being integrated in an outer race of the bearing, wherein using the oil piston includes applying the axial preload force on a flange of the outer race of the bearing.

6. The method as defined in claim 1 , wherein using the oil piston includes biasing axially an inner race of the bearing against a shoulder defined on the engine shaft to load the engine shaft in a direction of the axial preload force.

7. The method as defined in claim 1 , wherein using the oil piston includes supplying pressurized oil at a constant pressure on the outer race of the bearing to generate the axial preload force.

8. The method as defined in claim 1 , wherein the bearing of the bearing assembly is a first bearing, the bearing assembly including a second bearing, the first and second bearings mounted in a tandem configuration, the method comprising maintaining a fixed distance between the first and the second bearing in the tandem configuration while applying the axial preload force.

9. The method as defined in claim 8 , wherein using the oil piston includes applying the axial preload force on the first bearing and the second bearing in a rearward load direction along the engine shaft.

10. The method as defined in claim 8 , the first and second bearings having each having an inner race axially secured to the engine shaft, wherein applying the axial preload force on the first and second bearings in the rearward load direction includes biasing the engine shaft in the rearward load direction to compensate for a lack of aerodynamic load on the engine shaft.

11. A method of providing a preload force on a bearing of a bearing assembly, the bearing supporting a shaft in a gas turbine engine, the method comprising:

using an oil piston integrated into a flange of the bearing to apply an axial force on an outer race of the bearing, the axial force being applied continuously on the bearing during operation of the gas turbine engine, wherein applying the axial force on the outer race includes biasing axially an inner race of the bearing via rolling elements of the bearing interfacing between the outer race and the inner race against a complementary shoulder of the engine shaft to load the engine shaft in a rearward load direction along a rotation axis of the gas turbine engine.

12. The method as defined in claim 11 , wherein using the oil piston includes supplying pressurized oil at a constant pressure on the flange of the bearing.

13. The method as defined in claim 11 , wherein the flange at least partially circumscribes a piston cavity, the method comprising adjusting an oil pressure exerted on the flange to a desired pressure via an oil valve fluidly connected upstream of the piston cavity.

14. The method as defined in claim 11 , the bearing being a first bearing, the bearing assembly including a second bearing mounted in a tandem configuration with the first bearing, wherein using the oil piston includes biasing the first and the second bearings in a rearward load direction along a rotation axis of the gas turbine engine.

15. A bearing assembly for supporting an engine shaft, comprising:

a bearing having an inner race, an outer race and a series of rolling elements disposed between the inner race and the outer race, the inner race of the bearing coupled to the engine shaft, the outer race of the bearing defining a flange; and

an oil piston integrated into the bearing flange, the oil piston including a piston cavity, the bearing flange at least partially circumscribing the piston cavity, the oil piston configured to apply an axial preload force against the rolling elements of the bearing and in turn to the engine shaft coupled to the bearing inner race, wherein the bearing is a first bearing, the bearing assembly comprising a second bearing, the second bearing mounted to the engine shaft, the first bearing and the second bearing each having an inner race, the inner races of the first and second bearings axially secured to the engine shaft and contacting each other; and wherein the engine shaft defines a shoulder, the inner race of the first bearing abutting against the shoulder and the inner race of the second bearing abutting against the inner race of the first bearing.

16. The bearing assembly as defined in claim 15 , wherein the bearing has rolling elements interfacing between the outer race and an inner race, the flange being axially offset from the rolling elements, the flange extending radially outward from the rolling elements.

17. The bearing assembly as defined in claim 15 , wherein the inner races of the first and second bearing are clamped on each other between the shoulder and an axial fastener engaging the engine shaft.