Abstract: It is provided a control system for a gas turbine engine. Therein, at least one piezoelectric, in particular piezoresistive element arranged at a bearing adapted to support a shaft of the gas turbine engine is provided, wherein the piezoelectric element is adapted to provide information indicative for a force acting on the bearing to a processing unit, wherein the processing unit is adapted to determine a thrust force of the gas turbine engine based on the information provided by the piezoelectric element.

Abstract: A turbo engine, in particular a turbine for an airplane, is provided. The turbo engine is coupled with an energy harvesting device comprising at least one thermoelectric device for producing electric energy from temperature differences in the turbo engine and/or at least one kinetic energy converter for the conversion of vibrational energy into electric energy and wherein the energy harvesting device is coupled to a control system of the turbo engine as a redundant electric energy supply and/or the at least one kinetic energy converter providing a means for reducing the vibrational energy of the turbo engine. The invention also relates to an energy harvesting device and a method for energy harvesting.