System for performing staging control of a multi-stage combustor
A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds. The control system includes a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds. The control system further includes a controller which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split.
1. A fuel supply system for feeding fuel to a multi-stage combustor of a gas turbine engine, the fuel supply system comprising:
a plurality of fuel manifolds which distribute fuel to respective stages of the multi-stage combustor,
a fuel metering valve operable to control a rate at which fuel passes to the plurality of fuel manifolds,
an actuating arrangement which splits a fuel flow from the fuel metering valve between the plurality of fuel manifolds, and
a control system for performing staging control of the multi-stage combustor;
wherein the control system includes:
a fuel pressure sensor arrangement which senses one or more sensed fuel pressures including a fuel pressure at entry to the actuating arrangement and/or fuel pressures in one or more of the plurality of fuel manifolds; and
a controller which commands the fuel metering valve to supply fuel to the multi-stage combustor at a flow rate, and which repeatedly: (i) calculates a calculated fuel split between the plurality of fuel manifolds based on the one or more sensed fuel pressures, and (ii) issues a command signal to the actuating arrangement to implement the calculated fuel split, and
wherein the controller calculates:
(a) the calculated fuel split to divert fuel away from a particular manifold when the one or more sensed fuel pressures indicate that the fuel pressure in the particular manifold has exceeded a respective upper threshold pressure, and/or
(b) the calculated fuel split to divert fuel towards a particular manifold when the one or more sensed fuel pressures indicate that the fuel pressure in the particular manifold is below a respective lower threshold pressure.
2. The fuel supply system according to claim 1 , wherein the calculated fuel split is a first calculated fuel split;
wherein, when the first calculated fuel split corresponds to no change in a current fuel split, the controller further: (iii) calculates a calculated combustor flame temperature, and (iv) calculates a second calculated fuel split between the plurality of fuel manifolds based on the calculated combustor flame temperature to replace the first calculated fuel split; and
wherein the command signal issued to the actuating arrangement implements the second calculated fuel split in place of the first calculated fuel split.
3. The fuel supply system according to claim 1 , wherein:
the control system further includes an air pressure sensor which senses a sensed engine intake air pressure or a sensed ambient air pressure; and
the controller normalizes the sensed fuel pressure using the sensed engine intake air pressure or the sensed ambient air pressure before calculating the calculated fuel split.
4. The fuel supply system according to claim 1 , wherein the fuel distributed by the plurality of fuel manifolds is fed into the multi-stage combustor by a plurality of fuel injectors, and the control system further includes:
a health monitor which, based on the one or more sensed fuel pressures, diagnoses a fault in one of: a pneumatic pipe which extends from a high pressure compressor of the gas turbine engine, a fuel injector of the plurality of fuel injectors, the fuel metering valve, or a fuel flow demand to the fuel metering valve.
5. A gas turbine engine having a fuel supply system for feeding fuel to a multi-stage combustor of the gas turbine engine, the fuel supply system comprising:
a plurality of fuel manifolds which distribute fuel to respective stages of the multi-stage combustor,
a fuel metering valve operable to control a rate at which fuel passes to the plurality of fuel manifolds,
an actuating arrangement which splits a fuel flow from the fuel metering valve between the plurality of fuel manifolds, and
a control system for performing staging control of the multi-stage combustor;
wherein the control system includes:
a fuel pressure sensor arrangement which senses one or more sensed fuel pressures including a fuel pressure at entry to the actuating arrangement and/or fuel pressures in one or more of the plurality of fuel manifolds; and
a controller which commands the fuel metering valve to supply fuel to the multi-stage combustor at a flow rate, and which repeatedly: (i) calculates a calculated fuel split between the plurality of fuel manifolds based on the one or more sensed fuel pressures, and (ii) issues a command signal to the actuating arrangement to implement the calculated fuel split, and
wherein the controller calculates:
(a) the calculated fuel split to divert fuel away from a particular manifold when the one or more sensed fuel pressures indicate that the fuel pressure in the particular manifold has exceeded a respective upper threshold pressure, and/or
(b) the calculated fuel split to divert fuel towards a particular manifold when the one or more sensed fuel pressures indicate that the fuel pressure in the particular manifold is below a respective lower threshold pressure.