Aircraft engine control during icing of temperature probe

• US 8,560,203 B2
• Filed: 07/26/2011
• Issued: 10/15/2013
• Est. Priority Date: 07/30/2010
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Calandra, Salvatore, Giroux, Frederic, Iacobacci, Mark, Chabot, Martin, Syed, Yusuf, Chmiel, Dariusz, Bajaj, Adrienne, Hartropp, Simon
• Primary Examiner(s): Nguyen, John Q
• Assistant Examiner(s): Stroud, James E
• Application Number:
  US13/190,549
• Publication Number:
  US 20120029786A1
• Time in Patent Office: 812 Days
• Field of Search: 701/3, 701/8, 701/10, 701/14, 701/100, 244/134.R
• US Class Current: 701/100
• CPC Class Codes: B64D 31/06 actuated automatically
• CPC Class Codes: F01D 25/02 De-icing means for engines having icing phenomena
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02D 9/00 Controlling engines by throttling air or fuel-and-air induction conduits or exhaust conduits
• CPC Class Codes: F05B 2260/80 Diagnostics
• CPC Class Codes: F05B 2270/303 Temperature
• CPC Class Codes: F05D 2270/094 by using back-up controls
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: F05D 2270/80 Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
• CPC Class Codes: G01K 1/20 Compensating for effects of temperature changes other than those to be measured, e.g. changes in ambient temperature
• CPC Class Codes: G01K 13/02 for measuring temperature of moving fluids or granular materials capable of flow
• CPC Class Codes: G01K 13/022 Suction thermometers
• CPC Class Codes: G01K 13/024 of moving gases
• CPC Class Codes: G01K 2205/02 for measuring inlet gas temperature
• CPC Class Codes: G07C 3/00 Registering or indicating the condition or the working of machines or other apparatus, other than vehicles

Abstract

Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

Claims

1. A method for controlling an aircraft turbofan engine, the method performed by a data processor of a digital engine controller and comprising:

receiving one or more signals representative of temperature from a heated temperature probe;

using the one or more signals representative of temperature received from the heated temperature probe to generate one or more control signals for use in controlling the engine;

using the one or more signals representative of temperature received from the heated temperature probe, determining that an icing condition associated with the probe exists based at least partly on a rise in temperature at the heated temperature probe;

using data representing one or more substitute signals in place of the one or more signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine; and

causing the deactivation of a heating element associated with the probe.

2. The method as define in claim 1, wherein the rise in temperature includes the temperature rising at or exceeding a threshold rate.

3. The method as defined in claim 1, wherein the rise in temperature includes the temperature increasing by a threshold amount at or exceeding a threshold rate.

4. The method as defined in claim 1, wherein the substitute signal is representative of a temperature at or prior to the detection of the rise in temperature indicative of the icing condition.

5. The method as defined in claim 1, wherein the one or more substitute signals comprise one or more digitally synthesized signals representative of a substitute temperature.

6. The method as defined in claim 1, wherein the deactivation of the heating element is caused after a confirmation process in which a temperature associated with the heated temperature probe is determined to have stabilized at a temperature higher than an actual temperature.

7. The method as defined in claim 1, comprising using the one or more signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine after deactivation of the heating element.

8. The method as defined in claim 1, comprising using the one or more signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine following a determination that the temperature of the heated temperature probe has reached a temperature approximating an actual temperature.

9. The method as defined in claim 8, comprising transitioning a magnitude of the substitute signal towards a magnitude of the sensed signal.

10. A method for generating a signal useful in controlling an aircraft engine having an engine controller, the method comprising:

receiving a first signal representative of a total temperature of inlet air from a heated temperature probe;

using the first signal as a control parameter for generating a second signal useful in controlling the engine;

detecting, based on the first signal, a rise in temperature indicative of an icing condition of the probe;

using a substitute signal instead of the first signal as the control parameter for generating the second signal useful in controlling the engine;

deactivating a heating element associated with the probe; and

resuming to using the first signal as the control parameter for generating the second signal useful in controlling the engine.

11. The method as defined in claim 10, wherein the rise in temperature includes the temperature attaining a threshold temperature.

12. The method as define in claim 10, wherein the rise in temperature includes the temperature increasing at or exceeding a threshold rate.

13. The method as defined in claim 10, wherein the deactivation of the heating element occurs after a confirmation period during which the temperature from the first signal stabilizes at a temperature higher than an actual temperature.

14. The method as defined in claim 13, wherein the resumption to using the first signal as the control parameter occurs once the temperature from the first signal reaches a temperature approximating the actual temperature.

15. A device useful in controlling an aircraft turbine engine, the device comprising:

at least one digital processor configured to receive a first signal representative of a total temperature of inlet air using a heated temperature probe and use the first signal as a control parameter to generate a second signal useful in controlling the engine;

memory containing machine-readable instructions for execution by the at least one processor, the machine-readable instructions causing the at least one processor to;

detect, based on the first signal, a rise in temperature indicative of an icing condition of the probe;

use a substitute signal instead of the first signal as the control parameter for producing the second signal useful in controlling the engine; and

cause deactivation of a heater associated with the probe.

16. The device as defined in claim 15, wherein the substitute signal is representative of the temperature from the first signal at or prior to the detection of the rise in temperature indicative of the icing condition.

17. The device as defined in claim 15, wherein the deactivation of the heater associated with the probe is caused upon confirmation of the icing condition of the probe.

18. The device as defined in claim 15, wherein the memory contains machine-readable instructions to cause the at least one digital processor to resume the use of the first signal as the control parameter for producing the second signal useful in controlling the engine after the deactivation of the heater.