Systems and methods for filling a fuel manifold of a gas turbine engine
Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.
1. A method of operating a gas turbine engine including a primary fuel manifold and a secondary fuel manifold, the method comprising:
operating the gas turbine engine in a standby mode during which:
fuel is supplied to a combustor of the gas turbine engine via the primary fuel manifold;
the fuel is mixed with compressed air and is ignited; and
the secondary fuel manifold is partly or completely empty;
transitioning the gas turbine engine from the standby mode to an active mode by:
providing fuel flow to the secondary fuel manifold of the gas turbine engine to fill the secondary fuel manifold with fuel;
monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary fuel manifold; and
when a transition threshold is reached, reducing the fuel flow to the secondary fuel manifold and accelerating the gas turbine engine, the transition threshold being associated with the at least one engine operational parameter and being indicative that fuel has reached the combustor of the gas turbine engine via the secondary fuel manifold.
2. The method of claim 1 , wherein the at least one engine operational parameter comprises a rate of change of pressure at an outlet of a compressor of the gas turbine engine.
3. The method of claim 2 , wherein providing fuel flow to the secondary fuel manifold comprises providing the fuel flow in an open-loop fuel flow control scheme at a predefined rate.
4. The method of claim 3 , wherein accelerating the gas turbine engine comprises transitioning the open-loop fuel flow control scheme to a closed-loop fuel flow control scheme.
5. The method of claim 1 , wherein the at least one engine operational parameter comprises a rate of change of engine core spool speed.
6. The method of claim 5 , wherein providing fuel flow to the secondary fuel manifold comprises providing the fuel flow in a closed-loop fuel flow control scheme.
7. The method of claim 6 , wherein the transition threshold is a tracking error between the rate of change of engine core spool speed and an upper limit for the rate of change of engine core spool speed.
8. The method of claim 1 , wherein the at least one engine operational parameter comprises a pressure at an outlet of a compressor of the gas turbine engine.
9. The method of claim 8 , wherein the transition threshold is a difference between a synthesized value of the pressure at the outlet of the compressor and a sensed value of the pressure at the outlet of the compressor, the synthesized value generated by an engine model.
10. The method of claim 1 , wherein the at least one engine operational parameter comprises a ratio of commanded fuel flow to a pressure at an outlet of a compressor of the gas turbine engine.
11. A system for operating a gas turbine engine including a primary fuel manifold and a secondary fuel manifold, the system comprising:
a processing unit; and
a non-transitory computer-readable medium having stored thereon program instruction executable by the processing unit for:
causing the gas turbine engine to operate in a standby mode during which:
fuel is supplied to a combustor of the gas turbine engine via the primary fuel manifold;
the fuel is mixed with compressed air and is ignited; and
the secondary fuel manifold is partly or completely empty;
causing a transition of the gas turbine engine from the standby mode to an active mode by:
providing fuel flow to the secondary fuel manifold of the gas turbine engine to fill the secondary fuel manifold with fuel;
monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary fuel manifold; and
when a transition threshold is reached, reducing the fuel flow to the secondary fuel manifold and accelerating the gas turbine engine, the transition threshold being associated with the at least one engine operational parameter and being indicative that fuel has reached the combustor of the gas turbine engine via the secondary fuel manifold.
12. The system of claim 11 , wherein the at least one engine operational parameter comprises a rate of change of pressure at an outlet of a compressor of the gas turbine engine.
13. The system of claim 12 , wherein providing fuel flow to the secondary fuel manifold comprises providing the fuel flow in an open-loop fuel flow control scheme at a predefined rate.
14. The system of claim 13 , wherein accelerating the gas turbine engine comprises transitioning the open-loop fuel flow control scheme to a closed-loop fuel flow control scheme.
15. The system of claim 11 , wherein the at least one engine operational parameter comprises a rate of change of engine core spool speed.
16. The system of claim 15 , wherein providing fuel flow to the secondary fuel manifold comprises providing the fuel flow in a closed-loop fuel flow control scheme.
17. The system of claim 16 , wherein the transition threshold is a tracking error between the rate of change of engine core spool speed and an upper limit for the rate of change of engine core spool speed.
18. The system of claim 11 , wherein the at least one engine operational parameter comprises a pressure at an outlet of a compressor of the gas turbine engine.
19. The system of claim 18 , wherein the transition threshold is a difference between a synthesized value of the pressure at the outlet of the compressor and a sensed value of the pressure at the outlet of the compressor, the synthesized value generated by an engine model.
20. The system of claim 11 , wherein the at least one engine operational parameter comprises a ratio of commanded fuel flow to a pressure at an outlet of a compressor of the gas turbine engine.