Flight gas turbine with a first rotatable shaft

Abstract

The present invention describes an aircraft gas turbine with a first rotatable shaft and a second shaft arranged coaxially thereto and which at least in an area close to the shaft end is non-rotatably connected to the first shaft. Recesses are provided in shaft areas at a distance from the connecting area between the shafts, said recesses overlapping one another at least in some areas when a defined twist of the first shaft relative to the second shaft is exceeded. The shafts are assigned at least one lever element designed rotatable and engaging in the recesses of the shafts in the radial direction in the area of an end of the shafts and swivelling about a pivot point. A second lever arm of the lever elements is, when the first lever arm is engaged in the recesses, operatively connectable to an electric sensor device, in the area of which a sensor signal equivalent to the defined twist of the first shaft can be generated.

1 . Aircraft gas turbine with a first rotatable shaft, via which a torque can be exchanged between at least two assemblies, and a second shaft arranged coaxially thereto and which at least in an area close to the shaft end is non-rotatably connected to the first shaft, where recesses are provided in shaft areas at a distance from the connecting area between the shafts, said recesses overlapping one another at least in some areas when a twist of the first shaft relative to the second shaft, defined as a function of the torque applied in the area of the first shaft, is exceeded, where the shafts in the area of the recesses, are assigned at least one lever element designed rotatable about a pivot point fixed relative to the shaft and which engages in the recesses of the shafts in the radial direction in the area of an end of a lever arm, when there is a corresponding overlap of the recesses of the shafts, and swivels about the pivot point, with a radial distance between an end of a second lever arm of the lever element and the shafts increasing, characterized in that the second lever arm is, when the first lever arm is engaged in the recesses of the shafts, operatively connectable to an electric sensor device at least at some times, and a sensor signal equivalent to the defined twist of the first shaft can be generated in the area of the sensor device by making the operative connection. 
     
     
         2 . Aircraft gas turbine in accordance with  claim 1 , wherein the sensor device includes at least one electric switch or one electric sensor with cabling that can be brought into contact with the second lever arm. 
     
     
         3 . Aircraft gas turbine in accordance with  claim 2 , wherein the electric sensor is designed as a wire sensor and the second lever arm has a blade area operatively connectable to a signal wire, by means of which said signal wire can be severed. 
     
     
         4 . Aircraft gas turbine in accordance with  claim 1 , wherein the electric sensor is designed as a force sensor, using which the sensor signal can be generated upon contact between the second lever arm and the force sensor. 
     
     
         5 . Aircraft gas turbine in accordance with  claim 1 , wherein the sensor device is linked to a fuel shutoff valve, by means of which a fuel supply can be interrupted when the sensor signal equivalent to the defined twist of the first shaft is given.