Abstract: A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.

Abstract: The disclosure includes an apparatus comprising a diagnostic unit configured to communicate with a rules engine to determine whether a transmission detected in a vehicle is classified as unauthorized wireless device usage based on characteristics of RF signals received by a Detector Module collocated with the vehicle, geographic location data, and, optionally, additional secondary data, such determination being made by an external Rules Engine that is in communication with the Detector Module. The Rules Engine can provide instructions to and modify various threshold values used for preliminary RF signal analysis by the Detector Module.

Abstract: A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.

Abstract: A clutch device for a gas turbine engine having a sliding coupling mounted to the engine and slidingly displaceable therein. The sliding coupling is mountable between the gearbox and the output shaft. The sliding coupling is continuously engageable with the gearbox and is selectively engageable with the output shaft to mechanically couple the output shaft to the gearbox. The sliding coupling is slidingly displaceable between a first position in which the sliding coupling is mechanically coupled to the output shaft to transmit a rotational drive of the output shaft to the gearbox, and a second position in which the sliding coupling is disengaged from the output shaft. A piston is disposed within the engine and acts on the sliding coupling to displace the sliding coupling to at least the second position.

Abstract: A multi-engine system 10 for use on an aircraft 14 is disclosed. The system 10 may comprise a first aircraft engine 16A and a second aircraft engine 16B configured to drive at least one device 12 of the aircraft 14. A starter 20 may be coupled to one of the first and second aircraft engines 16A, 16B to assist starting of the one of the first and second aircraft engines 16A, 16B. An energy source 24 may be configured to deliver energy to the starter 20 at a rapid rate during rapid starting of the one of the first and the second aircraft engines 16A, 16B, the rapid rate being higher than a regular rate used during regular starting of the one of the first and the second aircraft engines 16A, 16B. The energy source 24 may comprise at least one supercapacitor.

Abstract: The disclosure includes an apparatus comprising a diagnostic unit configured to communicate with a rules engine to determine whether a transmission detected in a vehicle is classified as unauthorized wireless device usage based on characteristics of RF signals received by a Detector Module collocated with the vehicle, geographic location data, and, optionally, additional secondary data, such determination being made by an external Rules Engine that is in communication with the Detector Module. The Rules Engine can provide instructions to and modify various threshold values used for preliminary RF signal analysis by the Detector Module.

Abstract: Oil tanks for gas turbine engines and associated assembly methods are disclosed. In one exemplary embodiment, an oil tank is configured to be installed to occupy a radially-inner space defined by an annular radial air inlet duct of a reverse flow gas turbine engine. The oil tank may comprise a first tank portion and a second tank portion assembled together to cooperatively define an interior volume of the tank. An optional intermediate spacer may be disposed between the first tank portion and the second tank portion in order to form an oil tank of a larger size.

Abstract: The disclosure includes an apparatus comprising a diagnostic unit configured to communicate with a rules engine to determine whether a transmission detected in a vehicle is classified as driver wireless device usage based on passenger data indicating whether a passenger is present in the vehicle. The disclosure also includes a system comprising a shielding unit configured to transmit a noise signal to interrupt a transmission detected in a vehicle, and a diagnostic unit configured to communicate with a rules engine to determine whether the detected transmission is classified as driver wireless device usage based on the passenger data indicating whether a passenger is present in the vehicle, and activate a recording if the transmission is classified as driver wireless device usage.

Abstract: A method of bleeding air from a gas turbine engine having a compressor section with a downstream centrifugal compressor is described, which includes bleeding air from a first location upstream of the centrifugal compressor's outlet, when the compressor is operating in a first pressure range, and bleeding air from a second location upstream of the centrifugal compressor's outlet, when the engine is operating in a second pressure range.

Abstract: A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.

Abstract: Methods and systems for operating a turboprop engine having a high pressure spool and a low pressure spool rotating independently from one another. Each spool contains at least one compressor stage and the low pressure spool is connected to a propeller. The method comprises determining a target temperature-corrected rotational speed of the low pressure spool for a given set of operating parameters; and controlling a mechanical speed of the low pressure spool to maintain the temperature-corrected rotational speed of the low pressure spool substantially constant throughout at least a portion of a range of a power demand on the turboprop engine.

Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis extending through an accessory gear box (AGB). The LP spool has an LP compressor, which is axially positioned between the HP compressor of the HP spool and the AGB. A tower shaft drivingly connects the HP spool to the AGB.

Abstract: The disclosure includes an apparatus comprising a diagnostic unit configured to communicate with a rules engine to determine whether a transmission detected in a vehicle is classified as unauthorized wireless device usage based on characteristics of RF signals received by a Detector Module collocated with the vehicle, geographic location data, and, optionally, additional secondary data, such determination being made by an external Rules Engine that is in communication with the Detector Module. The Rules Engine can provide instructions to and modify various threshold values used for preliminary RF signal analysis by the Detector Module.

Abstract: There is described a method for and system for starting at least one engine from a twin engine installation.

Abstract: The disclosure includes an apparatus comprising a diagnostic unit configured to communicate with a rules engine to determine whether a transmission detected in a vehicle is classified as driver wireless device usage based on passenger data indicating whether a passenger is present in the vehicle. The disclosure also includes a system comprising a shielding unit configured to transmit a noise signal to interrupt a transmission detected in a vehicle, and a diagnostic unit configured to communicate with a rules engine to determine whether the detected transmission is classified as driver wireless device usage based on the passenger data indicating whether a passenger is present in the vehicle, and engage the shielding unit if the transmission is classified as driver wireless device usage.

Abstract: A reduction gearbox for an aircraft engine, including an input pinion configured to be driven by the aircraft engine, a input gear meshed with the input pinion, a drive gear meshed with the input gear, an output pinion, and an output gear meshed with the output pinion and configured to drive an output shaft of the aircraft engine. The reduction gearbox is selectively configurable between an engaged configuration where the input gear and output pinion are drivingly engaged and a disengaged configuration where the input gear is rotatable independently of the output pinion. The output shaft may drive a propeller and the gearbox may include a propeller brake. A method of driving a generator of a turboprop engine is also discussed.

Abstract: There is described a method and system for starting at least one engine from a twin engine installation having a first engine arrangement and a second engine arrangement. The method comprises receiving a first voltage level from a power source and increasing the first voltage level to a second voltage level; charging an energy storage unit having at least a first super-capacitor and a second super-capacitor to the second voltage level; selectively connecting one of the first super-capacitor and the second super-capacitor to a first power control unit in the first engine arrangement; controlling a discharge current to a first electric machine in the first engine arrangement via the first power control unit; and rotating a rotor of the first electric machine to an above engine idle speed to start a first engine of the twin engine installation.

Abstract: A method of operating a twin engine helicopter power plant, the power plant comprising: two turboshaft engines each having an engine shaft with a turbine at a distal end and a one-way clutch at a proximal end; a gear box having an input driven by the one way clutch of each engine and an output driving a helicopter rotor; a bypass clutch disposed between the proximal end of each engine shaft and the input of the gear box; and power plant management system controls for activating the bypass clutch; the method comprising: detecting when a rotary speed of an associated engine shaft is less than a rotary speed of the gear box input; activating the bypass clutch to drive the associated engine shaft using the rotation of the gear box input; and starting an associated engine by injecting fuel when the bypass clutch is activated.

Abstract: A gas turbine engine including at least one high pressure turbine rotor and at least one high pressure compressor rotor drivingly engaged to a rotatable high pressure spool, a low pressure spool rotatable independently of the high pressure spool, at least one low pressure turbine rotor drivingly engaged to the low pressure spool, and a rotatable load drivingly engaged to the low pressure spool. A fixed rotational speed ratio is defined between rotational speeds of the at high pressure turbine and compressor rotors. A fixed rotational speed ratio is defined between rotational speeds of the low pressure turbine rotor(s) and of the low pressure spool. A low pressure compressor rotor is in driving engagement with the low pressure spool through a variable transmission which defines a variable rotational speed ratio between the rotational speeds of the low pressure spool and of the low pressure compressor rotor.