Aircraft power outtake management

Patent metadata

Field	Value
Publication number	US-10280788-B2
Application number	US-201615175467-A
Country	US
Kind code	B2
Filing date	Jun 7, 2016
Priority date	Jul 12, 2012
Publication date	May 7, 2019
Grant date	May 7, 2019

Abstract

A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.

First claim

The invention claimed is:

1. A system for controlling a gas turbine engine supplying power to an aircraft, the system comprising:
a processor; and
a non-transitory computer readable medium having stored thereon programming instructions executable by the processor for:
receiving a measurement signal comprising a measurement of a power outtake of at least one load coupled to the engine, the power outtake corresponding to an amount of power drawn or consumed by the at least one load;
extracting the measurement from the measurement signal;
monitoring a condition of the engine based on the measurement;
generating, in accordance with the measurement, a control signal as a command to dynamically modify a power outtake threshold of the engine when any one of the following occurs: the engine reaches a thermal limit, a temperature overshoot level of the engine reaches a threshold, and an unpredicted event occurs; and
sending the control signal to the engine for dynamically modifying the power outtake threshold.

2. The system of claim 1 , wherein the control signal is generated when the unpredicted event occurs, the unpredicted event comprising a compressor or electrical surge condition affecting the engine.

3. The system of claim 1 , wherein the control signal is generated when the unpredicted event occurs, the unpredicted event comprising any one of a power surge, a generator overload, and an engine failure.

4. The system of claim 1 , wherein dynamically modifying the power outtake threshold comprises enforcing a power outtake limit defined in engine specifications.

5. The system of claim 1 , wherein dynamically modifying the power outtake threshold comprises limiting or stopping power extraction.

6. The system of claim 1 , wherein the at least one load is a plurality of loads, and wherein the programming instructions are further executable for increasing the power outtake threshold to a level that exceeds a limit defined in engine specifications when one or more loads of the plurality of loads are shed.

7. A method for controlling a gas turbine engine supplying power to an aircraft, the method comprising:
receiving a measurement signal comprising a measurement of a power outtake currently consumed by at least one load coupled to the engine;
extracting the measurement from the measurement signal;
monitoring a condition of the engine based on the measurement;
generating, in accordance with the measurement, a control signal as a command to dynamically modify a power outtake threshold of the engine when any one of the following occurs: the engine reaches a thermal limit, a temperature overshoot level of the engine reaches a threshold, and an unpredicted event occurs; and
sending the control signal to the engine for dynamically modifying the power outtake threshold.

8. The method of claim 7 , wherein the control signal is generated when the unpredicted event occurs, the unpredicted event comprising a compressor or electrical surge condition affecting the engine.

9. The method of claim 7 , wherein the control signal is generated when the unpredicted event occurs, the unpredicted event comprising any one of a power surge, a generator overload, and an engine failure.

10. The method of claim 7 , wherein dynamically modifying the power outtake threshold comprises enforcing a power outtake limit defined in engine specifications.

11. The method of claim 7 , wherein dynamically modifying the power outtake threshold comprises limiting or stopping power extraction.

12. The method of claim 7 , wherein the at least one load is a plurality of loads, and wherein dynamically modifying the power outtake threshold further comprises increasing the power outtake threshold to a level that exceeds a limit defined in engine specifications when one or more loads of the plurality of loads are shed.

13. A system for controlling a gas turbine engine supplying power to an aircraft, the system comprising:
means for receiving a measurement signal comprising a measurement of a power outtake currently consumed by at least one load coupled to the engine;
means for extracting the measurement from the measurement signal;
means for monitoring a condition of the engine based on the measurement;
means for generating,in accordance with the measurement, a control signal as a command to dynamically modify a power outtake threshold of the engine when any one of the following occurs: the engine reaches a thermal limit, a temperature overshoot level of the engine reaches a threshold, and an unpredicted event occurs; and
means for sending the control signal to the engine for dynamically modifying the power outtake threshold.

Assignees

• Pratt & Whitney Canada

Inventors

• Chen Bryan
• Chmiel Dariusz
• Beauchesne-Martel Philippe
• Jarvo James Robert

Classifications

• B64D31/06

  actuated automatically · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F05D2270/053

  Explicitly mentioned power · CPC title

• F05D2260/83

  Testing, e.g. methods, components or tools therefor · CPC title

• F02C7/042

  having variable geometry · CPC title