A controller for a gas turbine, wherein the gas turbine includes the compressor arranged to operate at a rotational speed n, the combustor and the fuel supply including the first fuel supply and the second fuel supply, wherein the compressor is arranged to provide air to the combustor at a steady state air mass flow rate m.sub.ss and wherein the fuel supply is arranged to supply fuel at a fuel mass flow rate m.sub.total to the combustor. The controller is arranged to, responsive to a load change L to the load L, control the compressor to provide air to the combustor at a new air mass flow rate m.sub.TR, wherein the new air mass flow rate m.sub.TR is within a range between a first threshold m.sub.LBO and a second threshold m.sub.SUR.

A braking system for the low pressure spool of a gas turbine engine includes a braking assembly connected to the low pressure spool and reversibly configurable between an actuated state and an unactuated state. The braking assembly in the unactuated state allows rotation of the low pressure spool without interference. The braking assembly in the actuated state applies a force opposing the rotation of the low pressure spool. A method of controlling the speed of rotation of a low pressure spool and a method of controlling the speed of rotation of low and high pressure spools are also discussed.

An emergency shut-off device shuts off supply of control oil to a trip-and-throttle valve of a steam turbine and closes the trip-and-throttle valve in an emergency. The emergency shut-off device includes: a cylinder; a piston that slides into the cylinder; a spring that applies a biasing force to the piston; a plurality of piston valves disposed on the piston; and a plurality of chambers that are formed by the piston valves. The control oil is supplied to and drained from the plurality of chambers, and a sliding surface of each of the piston valves has a groove to leak the control oil in a corresponding one of the chambers to another one of the chambers that is adjacent to the corresponding chamber in an axis direction.

In an embodiment, a rotorcraft includes: a plurality of engines; a flight control computer connected to the plurality of engines, the flight control computer being configured to: receive an operating parameter of a first engine of the plurality of engines; determine an engine output ramping rate for the first engine according to a difference between the operating parameter of the first engine and a nominal limit of the first engine; and increase the output of the first engine in response to detecting an outage of another engine of the plurality of engines, the output of the first engine being increased according to the engine output ramping rate.

The invention relates to a method for detecting a malfunction in a first turboshaft engine, referred to as an inoperative engine (4), of a twin-engine helicopter, and for controlling a second turboshaft engine, referred to as a healthy engine (5), each engine (4, 5) comprising protective stops regulated by a regulation device which define a maximum power regime, characterised in that it comprises: a step (10) of detecting an indication of failure of said inoperative engine (4); a step (11) of modifying said protective stops of said healthy engine (5) into protective stops which correspond to a maximum power single-engine regime, in the case of the detected indication of failure; a step (12) of confirming a failure of said inoperative engine (4); a step (13) of controlling an increase in the flow rate of fuel supply of said healthy engine (5), in the event of a confirmed failure.

A first fuel flow rate command value indicating a command value CSO of a fuel input amount is calculated so that the output of a gas turbine matches a target output. An upper limit value of the first fuel flow rate command value is calculated. The upper limit value of the first fuel flow rate command value is calculated on the basis of a deviation obtained by subtracting from an estimated value of the turbine inlet temperature of the gas turbine a second limit value relating to the estimated value set such that the estimated value does not exceed the first limit value of the turbine inlet temperature.

A trip system for a steam turbine closes a trip-and-throttle valve and a control valve of a steam turbine in an emergency. The trip system includes: an emergency shut-off device that shuts off supply of control oil for the trip-and-throttle valve and the control valve to close the trip-and-throttle valve and the control valve; and a drain device that includes a plurality of solenoid valves connected in parallel and drains the control oil by opening the solenoid valves. The emergency shut-off device includes a cylinder, a piston that slides in the cylinder, a spring that applies biasing force to the piston, a plurality of piston valves provided to the piston, and a plurality of chambers formed by the piston valves.

A control device (101) that controls a fuel gas supply system (100) that comprises: a compressor (1) that supplies compressed fuel gas to a load apparatus (15); an inflow amount regulating means (5) that regulates the amount of fuel gas that flows into the compressor (1); and an anti-surge valve (7) that is for returning to an inlet side of the compressor (1) fuel gas that is discharged from the compressor (1). The control device (101) comprises: a main pressure-control unit (101a) that controls the inflow amount regulating means (5) and the anti-surge valve (7) on the basis of a feedforward control value that is generated on the basis of the load of the load apparatus (15) and of a prescribed conversion process, and on the basis of a feedback control value that is generated on the basis of the deviation between a set value and a measured value for the discharge pressure of the compressor (1); and an emergency pressure-control unit (101b) that calculates a bias-added control value that is found by adding a predetermined bias value to an anti-surge valve control value that is for controlling the anti-surge valve (7) and that is calculated on the basis of at least one of the feedforward control value and the feedback control value, and that, on the basis of the occurrence of load variations that are at or above a prescribed value, switches between the anti-surge control value and the bias-added control value and controls the anti-surge valve (7).

The invention relates to an auxiliary system for mechanically driving a relay shaft (8) of a helicopter propulsion system, comprising: a hydraulic motor (7), mechanically connected to said relay shaft (8); a hydraulic circuit (10) for supplying a pressurised liquid to said hydraulic motor(7) a controlled, fast-opening hydraulic valve (11) arranged on the hydraulic circuit (10); a pyro-hydraulic storage unit (9) driven by a control unit (12) and connected to said hydraulic valve (11), said pyro-hydraulic storage unit (9)comprising: an enclosure (20) including a piston (16) that defines a main compartment (17) having at least one solid propellant cartridge (19) and a compartment (18) for a liquid supply; an ignition charge (25) connected to said main compartment (17) and suitable for initiating the combustion of at least one solid propellant cartridge (19) upon receiving a command from said control unit (12).

A dual trip manifold assembly (TMA) includes an isolation valve assembly having a first valve configured to receive a flow of fluid from a hydraulic system fluid supply. The first valve is configured to channel the flow of fluid to at least one hydraulic circuit. The isolation valve assembly also includes a second valve configured to receive the flow of fluid from the at least one hydraulic circuit of the at least two hydraulic circuits. The second valve is further configured to channel the fluid flow to a trip header and to receive the fluid flow from the trip header. The first valve and the second valve are synchronized to each other such that rotation of one of said first and second valves causes a substantially similar rotation in the other of said first and second valves header.