An electric power generation controller for use in an aircraft is a controller of an electric power generating apparatus including a manual transmission configured to change speed of rotational power of an aircraft engine, transmit the rotational power to an electric power generator, and switch a gear stage by a friction clutch pressed by an actuator. The electric power generation controller includes a manual transmission control section configured to control the manual transmission. The manual transmission control section includes: a shift command section configured to output a shift signal which switches the gear stage of the manual transmission; and a clutch control section configured to, when switching the gear stage of the manual transmission, control clutch pressure of the actuator such that the friction clutch becomes a half-engaged state.

An electric power generation controller for use in an aircraft to control an electric power generating apparatus including a manual transmission which changes speed of rotational power of an aircraft engine, transmits the rotational power to an electric power generator, and includes a plurality of gear stages. The electric power generation controller includes: a rotational frequency receiving section configured to receive an input rotational frequency or an output rotational frequency of the manual transmission as a monitoring rotational frequency; and a manual transmission control section configured to, when the monitoring rotational frequency exceeds a first threshold, output a shift-down signal to perform shift-down from an upper stage to a lower stage, and when the monitoring rotational frequency falls below a second threshold, output a shift-up signal to perform shift-up from the lower stage to the upper stage, the first threshold being set to a value larger than the second threshold.

An electric power generation controller for use in an aircraft is a controller of an electric power generating system configured such that: a manual transmission changes speed of rotational power of an aircraft engine; a continuously variable transmission changes the speed of the rotational power which has been changed in speed by the manual transmission; and the continuously variable transmission transmits the rotational power to an electric power generator. The electric power generation controller includes: a manual transmission control section configured to, when a predetermined shift condition is satisfied, control the manual transmission to switch a gear stage of the manual transmission; and a continuously variable transmission control section configured to, when the shift condition is satisfied, control the continuously variable transmission to such a side that fluctuation of an output rotational frequency of the manual transmission by the switching of the gear stage of the manual transmission is canceled.

A two-gas shaft turbine control system (31) is disclosed. The gas turbine control system comprises a fuel controller (35), which receives a speed error signal, indicating whether the low-pressure turbine wheel (11) of the gas turbine (1) is rotating at the desired target speed. The gas turbine control system (31) further comprises an NGV controller (41), which receives a speed error signal, indicating whether the high-pressure turbine wheel (9) of the gas turbine engine (1) is rotating at the desired target speed. Two cross channel controllers are further provided. On the basis of a gas turbine model, a first cross channel controller (43) provides a fuel control modification signal, which is added to a control signal generated by the fuel controller (35). A second cross channel controller (45) provides an NGV control modification signal. The modification signals are aimed at reducing or canceling the effect of mutual interaction between fuel control and NGV control. A two-shaft gas turbine engine system and a method of operation are further disclosed.

A method and system control the thrust of an aircraft turbomachine having a high bypass ratio by direct action on a variable-pitch system. The variable-pitch system varies the pitch of the vanes of a stator of a low-pressure compressor for the open-loop control of the thrust of the turbomachine. The method also provides closed-loop control of the pitch of the blades of a propeller based on a rotational speed of the propeller.

An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.

An electric power generation controller for use in an aircraft is a controller of an electric power generating apparatus including a manual transmission configured to change speed of rotational power of an aircraft engine, transmit the rotational power to an electric power generator, and switch a gear stage by a friction clutch pressed by an actuator. The electric power generation controller includes a manual transmission control section configured to control the manual transmission. The manual transmission control section includes: a shift command section configured to output a shift signal which switches the gear stage of the manual transmission; and a clutch control section configured to, when switching the gear stage of the manual transmission, control clutch pressure of the actuator such that the friction clutch becomes a half-engaged state.

An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.

A device for driving an integrated generator from an accessories relay box of a turbomachine. The device includes first and second electric motors arranged to transfer electric power from one to the other, one or more controllers configured for controlling said electric motors, and an epicyclic reduction gear train. The gear train includes a first element intended to be coupled to the accessories relay box, a second element intended to be coupled to the generator, and a third element driven to rotate by said first electric motor. The control means are configured to modify the speed of rotation of the third element in such a way that the second element is driven to rotate at a constant speed.

An aircraft propulsion system and computing system are provided. The propulsion system includes a low pressure (LP) spool and a core engine having a high pressure (HP) spool. A frame is positioned in serial flow arrangement between an HP turbine and an LP turbine. The frame includes an inter-turbine burner including a strut forming an outlet opening into a core flowpath of the propulsion system. A first fuel system is configured to flow a liquid fuel to a combustion section for generating first combustion gases. A second fuel system is configured to flow a gaseous fuel to the core flowpath via the inter-turbine burner for generating second combustion gases. The propulsion system forms a rated power output ratio of the core engine and the inter-turbine burner with the LP spool between 1.5 and 5.7.