Patent ID: 7322178

Claim:
A device for indicating a residual power margin of aircraft turbine engines, comprising: detecting means ( 7 ) associated with at least one turbine engine ( 2 a , 2 b ) of an aircraft to detect a number of first parameters (TQ, NG, ITT) related to a power output of the engine ( 2 a , 2 b ); calculating means ( 3 ) associated with the detecting means to calculate at least one second parameter (PI, PIa, PIb) indicating the power output of the engine ( 2 a , 2 b ) on the basis of said first parameters (TQ, NG, ITT); and display means ( 4 ); wherein said display means ( 4 ) comprise a power scale ( 20 ) having a plurality of reference indicators ( 23 , 24 , 25 ) indicating a plurality of operating limits (PL 1 , PL 2 , PL 3 ) of the engine ( 2 a , 2 b ); said plurality of operating limits including at least two of the following three operating limits; a continuous power limit (TOL 1 , NGL 1 , ITTL 1 ) indicating the maximum power that can be supplied continuously with no time limit; a term power limit (TQL 2 , NGL 2 , ITTL 2 ) which is higher than said continuous power limit (TQL 1 , NGL 1 , JTTL 1 ) and indicates the maximum power than can be supplied for at most a predetermined time interval; and a transient power limit (TQL 3 , NGL 3 , ITTL 3 ) which is higher than said term power limit (TQL 2 , NGL 2 , ITTL 2 ) and indicates the maximum power than can be supplied for emergency manoeuvres over a short transient period only and not exceeding a predetermined duration, said display means ( 4 ) further having at least one cursor ( 21 a , 21 b ) cooperating with and displayed next to said power scale ( 20 ) and said reference indicators ( 23 , 24 , 25 ) to simultaneously display a current value of the second parameter (PI, PIa, PIb) and an available power margin (M 1 , M 2 , M 3 ) of the engine ( 2 a , 2 b ), said available power margin defined as a difference between said second parameter and one of said reference indicators.