Adaptive engine acceleration for accessory loads

Patent metadata

Field	Value
Publication number	US-9944400-B2
Application number	US-201514618095-A
Country	US
Kind code	B2
Filing date	Feb 10, 2015
Priority date	Feb 11, 2014
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A method of adaptive engine acceleration for accessory loads includes receiving an accessory load indicator corresponding to an accessory load of an engine. The accessory load indicator is compared to an adjustment threshold. An acceleration rate of the engine is increased based on determining that the accessory load indicator is below the adjustment threshold. The acceleration rate of the engine is decreased based on determining that the accessory load indicator is above the adjustment threshold.

First claim

The invention claimed is:

1. A method of adaptive engine acceleration for accessory loads, the method comprising:
receiving an accessory load indicator corresponding to an accessory load of an engine;
comparing the accessory load indicator to an adjustment threshold;
adjusting an acceleration schedule of the engine by increasing the acceleration schedule when the accessory load indicator is below the adjustment threshold;
decreasing the acceleration schedule when the accessory load indicator is above the adjustment threshold; and
selecting an acceleration value for the aircraft from the adjusted acceleration schedule based on an acceleration demand.

2. The method of claim 1 , wherein the accessory load indicator is based on a sensed level of the accessory load driven by the engine.

3. The method of claim 2 , wherein the accessory load is crosschecked with respect to a second sensed accessory load of the engine.

4. The method of claim 1 , wherein adjusting the acceleration schedule is performed by applying a gain to one or more engine acceleration schedules.

5. The method of claim 4 , wherein adjusting the acceleration schedule further comprise cross-checking a sensed accessory load obtained at a first channel of an electronic engine control and with a sensed accessory load obtained at a second channel of the electronic engine control.

6. The method of claim 5 , wherein a first acceleration schedule adjustment is computed at the first channel and a second acceleration schedule adjustment is computed at the second channel, further comprising adjusting the one or more engine acceleration schedules based on confirming that the first acceleration schedule adjustment matches the second acceleration schedule adjustment.

7. The method of claim 6 , further comprising selecting a default engine acceleration schedule corresponding to a maximum accessory load when the first acceleration schedule adjustment does not match the second acceleration schedule adjustment.

8. The method of claim 1 , further comprising:
determining a magnitude of acceleration rate decrease based on decreasing the acceleration rate of the engine;
comparing the magnitude of acceleration rate decrease to a warning threshold; and
triggering a pilot warning of reduced acceleration capability based on determining that the magnitude of acceleration rate decrease is greater than the warning threshold.

9. The method of claim 1 , further comprising:
sharing engine acceleration schedule adjustments between electronic engine controls of the engine and a second engine.

10. The method of claim 1 , wherein the engine is on an aircraft and an adjustment magnitude of the acceleration rate of the engine is based a determination as to whether the aircraft is in-flight or grounded.

11. An engine control system comprising:
a processor; and
a memory having instructions stored thereon that, when executed by the processor, cause the engine control system to:
receive an accessory load indicator corresponding to an accessory load of an engine;
compare the accessory load indicator to an adjustment threshold;
adjust an acceleration schedule of the engine by increasing the acceleration schedule when the accessory load indicator is below the adjustment threshold;
decreasing the acceleration schedule when the accessory load indicator is above the adjustment threshold; and
select an acceleration value for the aircraft from the adjusted acceleration schedule based on an acceleration demand.

12. The engine control system of claim 11 , wherein the accessory load indicator is based on a sensed level of the accessory load driven by the engine and the sensed accessory load is crosschecked with respect to a second sensed accessory load of the engine.

13. The engine control system of claim 11 , wherein the adjustment the acceleration schedule is performed by applying a gain to one or more engine acceleration schedules.

14. The engine control system of claim 13 , wherein an adjustment to the acceleration schedule is determined by cross-checking a sensed accessory load obtained at a first channel of an electronic engine control and with a sensed accessory load obtained at a second channel of the electronic engine control.

15. The engine control system of claim 14 , wherein the one or more engine acceleration schedules are adjusted based on confirming that an acceleration schedule adjustment computed at the first channel matches an acceleration schedule adjustment computed at the second channel.

16. The engine control system of claim 15 , wherein a default version corresponding to a maximum accessory load is selected when the first acceleration schedule adjustment does not match the second acceleration schedule adjustment.

17. The engine control system of claim 11 , wherein the instructions further cause the engine control system to:
determine a magnitude of acceleration rate decrease based on the decrease of the acceleration rate of the engine;
compare the magnitude of acceleration rate decrease to a warning threshold; and
trigger a pilot warning of reduced acceleration capability based on determining that the magnitude of acceleration rate decrease is greater than the warning threshold.

18. The engine control system of claim 11 , wherein the engine is on an aircraft and an adjustment magnitude of the acceleration rate of the engine is based on a determination as to whether the aircraft is in-flight or grounded, and further wherein the instructions cause the engine control system to:
share engine acceleration schedule adjustments between electronic engine controls of the engine and a second engine.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Andrejczyk Robert J
• Sweet David H

Classifications

• B64D31/06 Primary

  actuated automatically · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• F02D41/1497

  With detection of the mechanical response of the engine · CPC title

• F02D41/021 Primary

  Introducing corrections for particular conditions exterior to the engine (conjoint control of vehicle sub-units for propelling the vehicle B60W30/18) · CPC title

• F02D29/02

  peculiar to engines driving vehicles; peculiar to engines driving variable pitch propellers · CPC title