Abstract: The present invention relates to a rotor of an electric machine for use in an aircraft. By forming the shaft of the rotor such that it performs, at least partially, the function of the back iron, components of the rotor can be combined. Further, by forming the rotor components in this manner, an internal shaft with an increased diameter can be used to provide a rotor with greater stiffness than equivalent prior art devices.

Abstract: A coolant system is arranged to be driven by a prime mover of an aircraft. The coolant system comprises a fluid circuit with a fluid therein, the fluid for cooling an electricity generator located in the fluid circuit. The fluid circuit comprises: a cooling path passing via at least one cooled component of the generator; a first fluid flow source configured to deliver a first fluid flow to the cooling path; a second fluid flow source configured to generate a second fluid flow; and a valve arrangement configured to selectively direct at least a proportion of the second fluid flow away from the cooling path in dependence on a measured operational parameter of the generator. An aircraft propulsion system and an aircraft can also include the coolant system.

Abstract: A method of manufacturing a rotor for a generator of an aircraft engine. The method includes providing a rotor body; mounting at least one magnet on the rotor body; wrapping a tow around the rotor body and the at least one magnet to form a wrapped tow having a plurality of layers overlaid in the radial direction; and curing the wrapped tow to form at least a part of a fibre-reinforced composite sleeve configured to retain the at least one magnet on the rotor body. The step of wrapping includes applying a controlled tension to the tow during wrapping. The controlled tension is varied according to the radial position of the layer being wrapped.

Abstract: The present invention relates to a generator drive disconnect device, of a generator arranged to be driven by an aircraft engine. The disconnect device comprises: a drive transfer means (1) having a first, connected configuration, and a second, disconnected configuration; a disconnect biasing means (200), configured to bias the drive transfer means to the disconnected configuration; and a fluid cavity (300), configured such that provision of a pressurised fluid in the fluid cavity biases the drive transfer means to the connected configuration.

Abstract: A generator arranged to be driven by an aircraft engine. The generator including a rotor. The rotor includes an inlet for receiving a fluid, a plurality of outlets configured to release the fluid from a radially outer region of the rotor, and a fluid distribution arrangement arranged to direct fluid from the inlet to one or more of the plurality of outlets. The fluid distribution arrangement is configured to selectively distribute fluid to one or more of the plurality of outlets in dependence on an operational parameter of the rotor.

Abstract: The present invention relates to a rotor of an electric machine for use in an aircraft. By forming the shaft of the rotor such that it performs, at least partially, the function of the back iron, components of the rotor can be combined. Further, by forming the rotor components in this manner, an internal shaft with an increased diameter can be used to provide a rotor with greater stiffness than equivalent prior art devices.

Abstract: The present invention relates to a generator drive disconnect device, of a generator arranged to be driven by an aircraft engine. The disconnect device comprises: a drive transfer means (1) having a first, connected configuration, and a second, disconnected configuration; a disconnect biasing means (200), configured to bias the drive transfer means to the disconnected configuration; and a fluid cavity (300), configured such that provision of a pressurised fluid in the fluid cavity biases the drive transfer means to the connected configuration.

Abstract: A generator arranged to be driven by an aircraft engine. The generator comprising a rotor. The rotor comprises an inlet for receiving a fluid, a plurality of outlets configured to release the fluid from a radially outer region of the rotor, and a fluid distribution arrangement arranged to direct fluid from the inlet to one or more of the plurality of outlets. The fluid distribution arrangement is configured to selectively distribute fluid to one or more of the plurality of outlets in dependence on an operational parameter of the rotor.

Abstract: A coolant system of a generator arranged to be driven by an aircraft engine. The coolant system includes a fluid circuit with a fluid therein, the fluid for cooling an electricity generator, and a pump, arranged to provide a flow of fluid around the fluid circuit to deliver coolant to at least one cooled component of the generator, via a cooler. The system also includes a fluid control device located between the pump and the cooler in the fluid circuit. The fluid control device is configured to selectively direct the fluid provided by the pump away from the cooler in dependence on a measured pressure in the fluid circuit. The measured pressure is derived from a measured point in the fluid circuit, the measured point being remote from the fluid control device.

Abstract: A novel method of manufacture and an improved construction of windings of a stator of an electrical machine are provided, which minimise the axial overhang length of the windings at an end of the stator. The invention further enables the conductor cross-section in the overhang region to be greater than when is passes through the core, which can improve overall electrical efficiency and thermal management in the stator. This is enabled by use of casting methods to cast pre-formed conductors outside of the stator core, and then inserting the cast conductors into slots of the stator core.

Abstract: A pump insert (50) for supporting a rotor (14) of a pump comprises an annular resilient support (52) for engaging the body (26) of the pump, the support (52) extending about a rolling bearing (10) having an inner race (12) for engaging the rotor (14), an axially preloaded outer race (16) fixed to the support (52), and a plurality of rolling elements (18) located between the races. During assembly, the rolling bearing (10) can be accurately positioned within the support (52) so that there is a very low tolerance stack-up when the insert (50) is fitted to the rotor (14). Consequently, the position of the rotor (14) will hardly change, if at all, when the rolling bearing (10) is replaced during servicing of the pump.

Abstract: A pump insert (50) for supporting a rotor (14) of a pump comprises an annular resilient support (52) for engaging the body (26) of the pump, the support (52) extending about a rolling bearing (10) having an inner race (12) for engaging the rotor (14), an axially preloaded outer race (16) fixed to the support (52), and a plurality of rolling elements (18) located between the races. During assembly, the rolling bearing (10) can be accurately positioned within the support (52) so that there is a very low tolerance stack-up when the insert (50) is fitted to the rotor (14). Consequently, the position of the rotor (14) will hardly change, if at all, when the rolling bearing (10) is replaced during servicing of the pump.

Abstract: A pump insert (50) for supporting a rotor (14) of a pump comprises an annular resilient support (52) for engaging the body (26) of the pump, the support (52) extending about a rolling bearing (10) having an inner race (12) for engaging the rotor (14), an axially preloaded outer race (16) fixed to the support (52), and a plurality of rolling elements (18) located between the races. During assembly, the rolling bearing (10) can be accurately positioned within the support (52) so that there is a very low tolerance stack-up when the insert (50) is fitted to the rotor (14). Consequently, the position of the rotor (14) will hardly change, if at all, when the rolling bearing (10) is replaced during servicing of the pump.

Abstract: A pump insert (50) for supporting a rotor (14) of a pump comprises an annular resilient support (52) for engaging the body (26) of the pump, the support (52) extending about a rolling bearing (10) having an inner race (12) for engaging the rotor (14), an axially preloaded outer race (16) fixed to the support (52), and a plurality of rolling elements (18) located between the races. During assembly, the rolling bearing (10) can be accurately positioned within the support (52) so that there is a very low tolerance stack-up when the insert (50) is fitted to the rotor (14). Consequently, the position of the rotor (14) will hardly change, if at all, when the rolling bearing (10) is replaced during servicing of the pump.