Device for indicating a residual power margin of aircraft turbine engines
A device for indicating a residual power margin of aircraft turbine engines includes a measuring stage associated with at least one turbine engine of an aircraft to measure a number of first parameters related to a power output of the engine; a calculating unit associated with the measuring unit to calculate at least one second parameter indicating the power output of the engine on the basis of the first parameters; and a display. The display includes a power scale having at least one reference indicator indicating an operating limit of the engine; and at least one cursor cooperating with the power scale and the reference indicator to simultaneously display a current value of the second parameter and an available power margin of the engine.
1. 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.
2. 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 at least one reference indicator ( 23 , 24 , 25 ) indicating an operating limit (PL 1 , PL 2 , PL 3 ) of the engine ( 2 a , 2 b ); and at least one cursor ( 21 a , 21 b ) cooperating with said power scale (20) and with said reference indicator ( 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 ),
and wherein said calculating means ( 3 ) comprise first scale conversion means ( 12 ) supplying third parameters (ETQ, ENG, EITT), each related to a respective one of said first parameters (TQ, NG, ITT); said third parameters (ETQ, ENG, EITT) being homogeneous and comparable with one another.
3. A device as claimed in claim 2 , characterized in that said calculating means ( 3 ) comprise selection means ( 14 ) associated with the first scale conversion means ( 12 ) and configured to supply a fourth parameter (EI) selectively related to the highest of said third parameters (ETQ, ENG, EITT) in first operating conditions, and to a predetermined one of said third parameters (ETQ, ENG, EITT) in second operating conditions.
4. A device as claimed in claim 3 , characterized in that, in said second operating conditions, said fourth parameter (EI) is related to a torque (TQ) supplied by the engine ( 2 a , 2 b ).
5. A device as claimed in claim 3 , characterized in that said calculating means ( 3 ) comprise second scale conversion means ( 15 ) associated with said selection means ( 14 ) and supplying said second parameter (PI, PIa, PIb) on the basis of said fourth parameter (EI).
6. A device as claimed in claim 5 , characterized in that said first scale conversion means ( 12 ) and said second scale conversion means ( 15 ) are interval-linear.
7. A device as claimed in claim 5 , characterized in that said first scale conversion means ( 12 ) and said second scale conversion means ( 15 ) are non-linear.
8. A device as claimed in claim 1 , characterized in that said power scale ( 20 ) comprises three reference indicators ( 23 , 24 , 25 ), each indicating a respective one of said three operating limits (PL 1 , PL 2 , PL 3 ) of the engine ( 2 a , 2 b ).