초록 ▼

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

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.

대표청구항 ▼

The invention claimed is: 1. A device for indicating a residual power margin of aircraft turbine engines, comprising: detecting means (7) associated with at least one turbine engine (2a, 2b) of an aircraft to detect a number of first parameters (TQ, NG, ITT) related to a power output of the engine

The invention claimed is: 1. A device for indicating a residual power margin of aircraft turbine engines, comprising: detecting means (7) associated with at least one turbine engine (2a, 2b) of an aircraft to detect a number of first parameters (TQ, NG, ITT) related to a power output of the engine (2a, 2b); 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 (2a, 2b) 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 (PL1, PL2, PL3) of the engine (2a, 2b); said plurality of operating limits including at least two of the following three operating limits; a continuous power limit (TOL1, NGL1, ITTL1) indicating the maximum power that can be supplied continuously with no time limit; a term power limit (TQL2, NGL2, ITTL2) which is higher than said continuous power limit (TQL1, NGL1, JTTL1) and indicates the maximum power than can be supplied for at most a predetermined time interval; and a transient power limit (TQL3, NGL3, ITTL3) which is higher than said term power limit (TQL2, NGL2, ITTL2) 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 (21a, 21b) 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 (M1, M2, M3) of the engine (2a, 2b), 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 (2a, 2b) of an aircraft to detect a number of first parameters (TQ, NG, ITT) related to a power output of the engine (2a, 2b); 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 (2a, 2b) 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 (PL1, PL2, PL3) of the engine (2a, 2b); and at least one cursor (21a, 21b) 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 (M1, M2, M3) of the engine (2a, 2b), 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 (2a, 2b). 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 (PL1, PL2, PL3) of the engine (2a, 2b).