Bowed rotor start response damping system

1. A method of bowed rotor start response damping for a gas turbine engine, the method comprising:

selectively modifying a spring rate and a damping characteristic of one or more bearing supports in the gas turbine engine by controlling a release of pressurized oil from an accumulator comprising a pressurizing reservoir having a variable volume while a shaft of the gas turbine engine rotates below a rotational speed which adversely affects the gas turbine engine during a bowed rotor condition of the gas turbine engine.

2. The method of claim 1 , wherein selectively modifying the spring rate and the damping characteristic of the one or more bearing supports is performed while the shaft of the gas turbine engine rotates at a changing rotational speed that passes through a resonant frequency of the shaft.

3. The method of claim 1 , wherein the gas turbine engine comprises a turbofan with a straddle mounted starting spool comprising at least one bearing located aft of at least one turbine disk of the gas turbine engine.

4. The method of claim 1 , wherein the gas turbine engine comprises a turbofan.

5. The method of claim 1 , wherein selectively modifying the spring rate and the damping characteristic of the one or more bearing supports is performed based on detecting a start indication of the gas turbine engine.

6. The method of claim 5 , wherein selectively modifying the spring rate and the damping characteristic of the one or more bearing supports further comprises opening a control valve to urge pressurized oil into a damper of at least one of the one or more bearing supports based on the start indication.

7. The method of claim 6 , further comprising selectively closing the control valve to accumulate the pressurized oil in the pressurizing reservoir.

8. A bowed rotor start response damping system for a gas turbine engine, the bowed rotor start response damping system comprising:

an accumulator comprising a pressurizing reservoir having a variable volume; and

an oil supply circuit configured to selectively modify a spring rate and a damping characteristic of one or more bearing supports in the gas turbine engine by controlling a release of pressurized oil from the accumulator while a shaft of the gas turbine engine rotates below a rotational speed which adversely affects the gas turbine engine during a bowed rotor condition of the gas turbine engine.

9. The bowed rotor start response damping system of claim 8 , wherein selective modification of the spring rate and the damping characteristic of the one or more bearing supports is performed while the shaft of the gas turbine engine rotates at a changing rotational speed that passes through a resonant frequency of the shaft.

10. The bowed rotor start response damping system of claim 8 , wherein the gas turbine engine comprises a turbofan with a straddle mounted starting spool comprising at least one bearing located aft of at least one turbine disk of the gas turbine engine.

11. The bowed rotor start response damping system of claim 8 , wherein the gas turbine engine comprises a geared turbofan.

12. The bowed rotor start response damping system of claim 8 , wherein selective modification of the spring rate and the damping characteristic of the one or more bearing supports are performed based on detecting a start indication of the gas turbine engine.

13. The bowed rotor start response damping system of claim 12 , further comprising a control valve, wherein selective modification of the spring rate and the damping characteristic of the one or more bearing supports further comprises opening the control valve to urge pressurized oil into a damper of at least one of the one or more bearing supports based on the start indication.

14. The bowed rotor start response damping system of claim 13 , wherein the control valve is selectively closed to accumulate the pressurized oil in the pressurizing reservoir.

15. A gas turbine engine comprising:

one or more bearing supports;

a shaft supported by one or more bearings of the one or more bearing supports;

an accumulator comprising a pressurizing reservoir having a variable volume; and

an oil supply circuit configured to selectively modify a spring rate and a damping characteristic of the one or more bearing supports by controlling a release of pressurized oil from the accumulator while the shaft rotates below a rotational speed which adversely affects the gas turbine engine during a bowed rotor condition of the gas turbine engine.

16. The gas turbine engine of claim 15 , wherein selective modification of the spring rate and the damping characteristic of the one or more bearing supports is performed while the shaft of the gas turbine engine rotates at a changing rotational speed that passes through a resonant frequency of the shaft.

17. The gas turbine engine of claim 15 , wherein the gas turbine engine comprises a turbofan with a straddle mounted starting spool comprising at least one bearing located aft of at least one turbine disk of the gas turbine engine.

18. The gas turbine engine of claim 15 , wherein the gas turbine engine comprises a geared turbofan.

19. The gas turbine engine of claim 15 , wherein selective modification of the spring rate and the damping characteristic of the one or more bearing supports are performed based on detecting a start indication of the gas turbine engine.

20. The gas turbine engine of claim 19 , further comprising a control valve, wherein selective modification of the spring rate and the damping characteristic of the one or more bearing supports further comprises opening the control valve to urge pressurized oil into a damper of at least one of the one or more bearing supports based on the start indication, and the control valve is selectively closed to accumulate the pressurized oil in the pressurizing reservoir.