flow through the compressor which will compensate for the mass of air lost through the hole 39 the effect of the former increase is not so simple to explain but can in general be explained by the fact that the energy extracted by a turbine is related to the temperature drop across it if the inlet temperature of the two turbine system of fig2 is increased then in general those turbines will extract more energy fig3 is a flow chart illustrating a generalized process undertaken by the invention block 100 represents the collective outputs of the engine sensors the modern gas turbine aircraft engine is equipped with an array of numerous sensors which measure temperatures and pressures at various locations and the speeds of the rotors many of the sensors termed prime sensors are equipped with back up sensors which provide redundancy in the event that the prime sensors fail the sensor outputs are received by the engine control not shown as indicated by block 105 block 110 represents the engine control procedures or algorithms which are implemented by the engine control the inventors point out that block 110 is a simplification and the actual control system and its processes are quite complex engine control systems generally are well known the control system controls various operating conditions of the engine 3 such as 1 fuel air ratio 2 stator vane angle 3 compressor bleeds 4 turbine shroud cooling and so on these controlled.