Abstract: Systems and methods are disclosed that provide smart alerts to users, e.g., alerts to users about diabetic states that are only provided when it makes sense to do so, e.g., when the system can predict or estimate that the user is not already cognitively aware of their current condition, e.g., particularly where the current condition is a diabetic state warranting attention. In this way, the alert or alarm is personalized and made particularly effective for that user. Such systems and methods still alert the user when action is necessary, e.g., a bolus or temporary basal rate change, or provide a response to a missed bolus or a need for correction, but do not alert when action is unnecessary, e.g., if the user is already estimated or predicted to be cognitively aware of the diabetic state warranting attention, or if corrective action was already taken.

Abstract: A gas turbine engine for an aircraft, including the following: a core engine including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan, which is positioned upstream of the core engine, wherein the fan includes a plurality of fan blades; and a gear box which can be driven by the core shaft, wherein the fan can be driven at a lower rotational speed than the core shaft by means of the gear box, wherein the core shaft is designed as a drive shaft for the gear box and has at least one axial first region which has a diameter greater than the diameter of at least one axial second region, wherein the at least one first region is arranged axially between the drive side of the gear box and a mounting and/or attachment on a static part of the gas turbine engine.

Abstract: The invention relates to a stabilization bearing system for a geared turbofan engine, in particular an aircraft engine, with a stabilization bearing for an input shaft device to an epicyclic gearbox device of the geared turbofan engine, the stabilization bearing being located axially in front of an input shaft device location bearing system.

Abstract: A gas turbine engine for an aircraft, including the following: a core engine including a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan, which is positioned upstream of the core engine, wherein the fan includes a plurality of fan blades; and a gear box which can be driven by the core shaft, wherein the fan can be driven at a lower rotational speed than the core shaft by means of the gear box, wherein the core shaft is designed as a drive shaft for the gear box and has at least one axial first region which has a diameter greater than the diameter of at least one axial second region, wherein the at least one first region is arranged axially between the drive side of the gear box and a mounting and/or attachment on a static part of the gas turbine engine.

Abstract: The embodiments relate to devices for coupling, in particular the recoupling an output shaft with an epicyclic gearbox in a gas turbine engine, wherein an axial coupling action between the output shaft and the epicyclic gearbox is generatable through an oil pump and transmitted through an oil transfer coupling. Embodiments also relate to a method for coupling and a gas turbine engine.

Abstract: The invention relates to a stabilization bearing system for a geared turbofan engine, in particular an aircraft engine, with a stabilization bearing for an input shaft device to an epicyclic gearbox device of the geared turbofan engine, the stabilization bearing being located axially in front of an input shaft device location bearing system.