System and method for operating a multi-engine rotorcraft for ice accretion shedding

Patent metadata

Field	Value
Publication number	US-11535386-B2
Application number	US-201916671551-A
Country	US
Kind code	B2
Filing date	Nov 1, 2019
Priority date	Jun 17, 2019
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.

First claim

The invention claimed is:

1. A method for operating a multi-engine rotorcraft, the method comprising:
when the rotorcraft is cruising in an asymmetric operating regime (AOR) in which at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of increasing a power level of the at least one second engine and moving at least one variable geometry mechanism of the at least one second engine to shed any ice accumulation on the at least one second engine.

2. The method of claim 1 , further comprising determining whether one or more conditions are present in which the ice accumulation on the at least one second engine is possible.

3. The method of claim 2 , wherein determining whether the one or more conditions are present is performed on the basis of outside air temperature.

4. The method of claim 3 , wherein determining whether the one or more conditions are present is further performed on the basis of at least one of a power level of the at least one second engine, a temperature at an inlet of the at least one second engine, an angle of at least one variable guide of the at least one second engine, a mass flow of the at least one second engine, a core corrected speed of the at least one second engine, ambient pressure, airspeed, and an altitude of the rotorcraft.

5. The method of claim 2 , wherein determining whether the one or more conditions are present is performed on the basis of measurement data received from at least one icing sensor provided on the rotorcraft.

6. The method of claim 2 , wherein determining whether the one or more conditions are present comprises:
receiving measurement data from at least one pressure sensor provided on the at least one second engine;
comparing the measurement data to a predetermined threshold; and
responsive to determining that the measurement data exceeds the threshold, determining that the ice accumulation is possible.

7. The method of claim 6 , wherein determining whether the one or more conditions are present is performed on the basis of measurement data received from a pressure differential sensor configured to measure pressure at a protection grid provided at an inlet of the second engine.

8. The method of claim 6 , wherein determining whether the one or more conditions are present is performed on the basis of measurement data received from a pressure differential sensor configured to measure pressure on either side of a plurality of inlet guide vanes of the second engine.

9. The method of claim 2 , wherein determining whether the one or more conditions are present is performed on the basis of input data received from at least one thermodynamic indicator provided on the rotorcraft.

10. The method of claim 2 , wherein determining whether the one or more conditions are present is performed on the basis of input data acquired from at least one operator input.

11. The method of claim 1 , wherein increasing the power level of the at least one second engine comprises increasing a fuel flow to the at least one second engine.

12. The method of claim 1 , wherein moving the at least one variable geometry mechanism of the at least one second engine comprises opening a plurality of variable inlet guide vanes of the at least one second engine.

13. The method of claim 1 , wherein moving the at least one variable geometry mechanism of the at least one second engine comprises opening a plurality of handling bleed-off valves of the at least one second engine.

14. The method of claim 1 , wherein the at least one of increasing the power level of the at least one second engine and moving the at least one variable geometry mechanism of the at least one second engine is performed periodically.

15. The method of claim 1 , wherein the at least one of increasing the power level of the at least one second engine and moving the at least one variable geometry mechanism of the at least one second engine is performed in a single occurrence.

16. A system for operating a multi-engine rotorcraft, comprising:
a processing unit; and
a non-transitory computer-readable medium having stored thereon program instructions executable by the processing unit for:
when the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of increasing a power level of the at least one second engine and moving at least one variable geometry mechanism of the at least one second engine to shed any ice accumulation on the at least one second engine.

17. The system of claim 16 , wherein the program instructions are executable by the processing unit for determining whether one or more conditions are present in which the ice accumulation on the at least one second engine is possible.

18. The system of claim 17 , wherein the program instructions are executable by the processing unit for determining whether the one or more conditions are present on the basis of outside air temperature.

19. The system of claim 18 , wherein the program instructions are executable by the processing unit for determining whether the one or more conditions are present on the basis of at least one of a power level of the at least one second engine, an inlet temperature of the at least one second engine, an angle of at least one variable guide of the at least one second engine, a mass flow of the at least one second engine, a core corrected speed of the at least one second engine, ambient pressure, airspeed, and an altitude of the rotorcraft.

20. The system of claim 17 , wherein the program instructions are executable by the processing unit for determining whether the one or more conditions are present comprising:
receiving measurement data from a pressure differential sensor provided on the at least one second engine, the pressure differential sensor configured to measure pressure on either side of a plurality of inlet guide vanes of the second engine;
comparing the measurement data to a predetermined threshold; and
responsive to determining that the measurement data exceeds the threshold, determining that the ice accumulation is possible.

21. The system of claim 17 , wherein the program instructions are executable by the processing unit for determining whether the one or more conditions are present comprising:
receiving measurement data from a pressure differential sensor provided on the at least one second engine, the pressure differential sensor configured to measure pressure at a protection grid provided at an inlet of the second engine;
comparing the measurement data to a predetermined threshold; and
responsive to determining that the measurement data exceeds the threshold, determining that the ice accumulation is possible.

22. The system of claim 16 , wherein the program instructions are executable by the processing unit for outputting at least one control signal comprising instructions for at least one of increasing a fuel flow to the at least one second engine to increase the power level of the at least one second engine and opening a plurality of variable inlet guide vanes of the at least one second engine.

Assignees

• Pratt & Whitney Canada

Inventors

• Beauchesne-Martel Philippe
• Cunningham Mark

Classifications

• F02C6/02

  Plural gas-turbine plants having a common power output · CPC title

• B64D15/22

  Automatic initiation by icing detector · CPC title

• F05D2220/74

  a gas turbine · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F05D2270/09

  to cope with emergencies · CPC title