Emergency shut-down detection system for a gas turbine

A gas turbine engine comprising:

• a fan;
• an IP compressor arranged aft of the fan:
• an HP compressor arranged aft of the IP compressor;
• a combustor arranged aft of the HP compressor;
• an HP turbine arranged aft of the combustor and coupled to said HP compressor by an HP spool;
• a bearing assembly comprising a bearing mounted on the HP Spool, the bearing assembly supporting an inner housing, an outer housing and a spring bar assembly arranged between the inner housing and the outer housing, the spring bar assembly having a plurality of circumferentially disposed spring bars configured to flex, the outer housing having a protrusion;
• at least one electrical speed sensor arranged fore of said HP compressor and near the protrusion, the at least one electrical speed sensor operable to provide a compressor speed signal, said at least one speed sensor including an electrical continuity circuit operable to generate a continuity signal for the electrical speed sensor;
• a controller having a number of inputs for receiving at least one measured engine parameter and a number of outputs for transmitting control signals for controlling engine operation variables, said controller including an input for receiving the speed signal and the continuity signal;
• wherein when the HP spool fractures, the HP compressor generates a forward axial force to fracture the spring bars causing the protrusion to sever the at least one speed probe resulting in a simultaneous termination of the compressor speed signal and continuity signal.