Gas turbine acceleration limit biasing for premature asymmetric operating regime exits

1 . A method, comprising:

sending a first control signal, wherein the first control signal causes a turbine engine of a plurality of turbine engines of an aircraft to initiate an entry into an asymmetric operating regime;

receiving, a control input for an exit from the asymmetric operating regime;

determining, a progression state of the turbine engine into the asymmetric operating regime;

sending a second control signal for accelerating the turbine engine to a high-power operating regime, wherein the second control signal specifies an acceleration rate based on the progression state of the turbine engine into the asymmetric operating regime;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is a complete entry into the asymmetric operating regime, specifying a first acceleration rate as the acceleration rate; and

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, specifying a second acceleration rate as the acceleration rate,

wherein the first acceleration rate is greater than the second acceleration rate.

2 . The method of claim 1 , wherein the progression state of the turbine engine into the asymmetric operating regime is determined based on a current value of a measured speed of the turbine engine.

3 . The method of claim 1 , wherein the progression state of the turbine engine into the asymmetric operating regime is determined based on at least one of: a time elapsed since sending the first control signal, a current value of a measured power of the turbine engine, a measured pressure within the turbine engine, or a measured temperature within the turbine engine.

4 . The method of claim 1 , further comprising:

obtaining a nominal acceleration rate;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is the complete entry into the asymmetric operating regime, specifying the nominal acceleration rate as the first acceleration rate; and

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, biasing the nominal acceleration rate downwards to obtain the second acceleration rate.

5 . The method of claim 4 , wherein the nominal acceleration rate is determined based on at least one of a current airspeed or a current altitude.

6 . The method of claim 4 , further comprising:

determining a value expressing the progression state of the turbine engine into the asymmetric operating regime;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, determining a bias value for the value expressing the progression state of the turbine engine into the asymmetric operating regime; and

applying the determined bias value to the nominal acceleration rate to obtain the second acceleration rate.

7 . An apparatus, comprising:

an input/output interface;

a processor, wherein the processor is configured to:

send a first control signal, wherein the first control signal causes a turbine engine of a plurality of turbine engines of an aircraft to initiate an entry into an asymmetric operating regime;

receive, a control input for an exit from the asymmetric operating regime;

determine, a progression state of the turbine engine into the asymmetric operating regime;

send a second control signal for accelerating the turbine engine to a high-power operating regime, wherein the second control signal specifies an acceleration rate based on the progression state of the turbine engine into the asymmetric operating regime;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is a complete entry into the asymmetric operating regime, specify a first acceleration rate as the acceleration rate; and

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, specify a second acceleration rate as the acceleration rate,

wherein the first acceleration rate is greater than the second acceleration rate.

8 . The apparatus of claim 7 , wherein the progression state of the turbine engine into the asymmetric operating regime is determined based on a current value of a measured speed of the turbine engine.

9 . The apparatus of claim 7 , wherein the progression state of the turbine engine into the asymmetric operating regime is determined based on at least one of: a time elapsed since sending the first control signal, a current value of a measured power of the turbine engine, a measured pressure within the turbine engine, or a measured temperature within the turbine engine.

10 . The apparatus of claim 7 , wherein the processor is further configured to:

obtain a nominal acceleration rate;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is the complete entry into the asymmetric operating regime, specify the nominal acceleration rate as the first acceleration rate; and

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, bias the nominal acceleration rate downwards to obtain the second acceleration rate.

11 . The apparatus of claim 10 , wherein the nominal acceleration rate is determined based on at least one of a current airspeed or a current altitude.

12 . The apparatus of claim 10 , wherein the processor is further configured to:

determine a value expressing the progression state of the turbine engine into the asymmetric operating regime;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, determine a bias value for the value expressing the progression state of the turbine engine into the asymmetric operating regime; and

apply the determined bias value to the nominal acceleration rate to obtain the second acceleration rate.

13 . A non-transitory computer-readable medium containing instructions, which when executed by a processor, cause an apparatus to:

send a first control signal, wherein the first control signal causes a turbine engine of a plurality of turbine engines of an aircraft to initiate an entry into an asymmetric operating regime;

receive, a control input for an exit from the asymmetric operating regime;

determine, a progression state of the turbine engine into the asymmetric operating regime;

send a second control signal for accelerating the turbine engine to a high-power operating regime, wherein the second control signal specifies an acceleration rate based on the progression state of the turbine engine into the asymmetric operating regime;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is a complete entry into the asymmetric operating regime, specify a first acceleration rate as the acceleration rate; and

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, specify a second acceleration rate as the acceleration rate,

wherein the first acceleration rate is greater than the second acceleration rate.

14 . The non-transitory computer-readable medium of claim 13 , wherein the progression state of the turbine engine into the asymmetric operating regime is determined based on a current value of a measured speed of the turbine engine.

15 . The non-transitory computer-readable medium of claim 13 , wherein the progression state of the turbine engine into the asymmetric operating regime is determined based on at least one of: a time elapsed since sending the first control signal, a current value of a measured power of the turbine engine, a measured pressure within the turbine engine, or a measured temperature within the turbine engine.

16 . The non-transitory computer-readable medium of claim 13 , further comprising instructions, which, when executed by the processor, cause the apparatus to:

obtain a nominal acceleration rate;

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is the complete entry into the asymmetric operating regime, specify the nominal acceleration rate as the first acceleration rate; and

responsive to determining that the progression state of the turbine engine into the asymmetric operating regime is incomplete, bias the nominal acceleration rate downwards to obtain the second acceleration rate.

17 . The non-transitory computer-readable medium of claim 16 , wherein the nominal acceleration rate is determined based on at least one of a current airspeed or a current altitude.