Gas turbine acceleration limit biasing for premature asymmetric operating regime exits
AssigneePratt & Whitney Canada Corp.
InventorsLouis Duranleau-Hendrickx, Andrea Henning
Life of this patent
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Abstract
A method includes 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. The method further includes 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, and sending a second control signal for accelerating the turbine engine to a high-power operating regime, wherein the second control signal specifies a acceleration rate based on the progression state of the turbine engine into the asymmetric operating regime.
Claims17
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.
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.
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.
Dependencies are inferred from the claim text.