Method and device for optimizing the utilization of an engine

Patent metadata

Field	Value
Publication number	US-9284885-B2
Application number	US-201514837151-A
Country	US
Kind code	B2
Filing date	Aug 27, 2015
Priority date	Aug 31, 2010
Publication date	Mar 15, 2016
Grant date	Mar 15, 2016

Abstract

A method of optimizing the use of an aircraft power plant having at least one engine operating within a performance envelope covering at least a first rating and a second rating, the first rating presenting a first power (P1) usable over a predetermined first time interval (D1), the second rating presenting a second power (P2) greater than said first power (P1), the second power (P2) being usable continuously over a predetermined second time interval (D2). Thus, while the engine is developing a third power (P3) that is both greater than the first power (P1) and less than or equal to the second power (P2), a potential first duration of utilization (ΔT) of continuous use of the second power (P2) is determined and displayed, the first duration of utilization (ΔT) elapsing at a speed that is variable and that depends on said third power (P3).

First claim

What is claimed is:

1. A method of optimizing the use of an aircraft power plant having at least one engine, the method comprising:
operating the engine within a performance envelope covering at least a first rating and a second rating, the first rating presenting a first power (P1) which the engine can develop over a predetermined first time interval (D1), the second rating presenting a second power (P2) greater than the first power (P1) which the engine can develop continuously over a predetermined second time interval (D2) shorter in duration than the first time interval;
operating the engine to develop a third power (P3) greater than the first power (P1) and less than the second power (P2);
while the engine is developing the third power (P3), determining a potential first duration of utilization (ΔT) of the engine to develop continuously the second power (P2) which takes into account engine deterioration caused while the engine is developing the third power (P3) relative to engine deterioration which would be caused if the engine developed the second power (P2) instead of the third power (P3) whereby the first duration of utilization (ΔT) is a third time interval longer in duration than the second time interval and shorter in duration than the first time interval, and displaying on a display the first duration of utilization (ΔT) in the form of a countdown which elapses at a speed that is variable and that depends on the third power (P3) relative to the second power (P2) such that a pilot can be apprised from the countdown of a remaining duration that the engine can be operated to develop continuously the second power (P2);
controlling the operation of the engine using information provided by the countdown; and
wherein the method amounts to creating for the performance envelope a third rating presenting the third power (P3) which the engine can develop continuously over the third time interval with the first rating, the second rating, and time between overhauls (TBO) for which the engine is certified remaining unchanged.

2. The method according to claim 1 , wherein the closer the third power (P3) comes to the second power (P2), the faster the first duration of utilization (ΔT) elapses.

3. The method according to claim 1 , wherein the power plant has two engines and the first duration of utilization (ΔT) is determined for each engine, with the smaller first duration of utilization (ΔT) being displayed.

4. The method according to claim 1 , wherein a warning is triggered when the first duration of utilization (ΔT) becomes less than a first predetermined threshold.

5. The method according to claim 1 , wherein a second potential duration of continuous utilization (ΔT′) of a third power (P3) developed at a current instant (TPS) is determined and displayed, the third power (P3) being greater than the first power (P1) and less than the second power (P2), the second duration of utilization (ΔT′) depending on the third power (P3).

6. The method according to claim 5 , wherein the power plant has two engines and the second duration of utilization (ΔT′) is determined for each engine, with the smaller second duration of utilization (ΔT′) being displayed.

7. The method according to claim 5 , wherein a warning is triggered when the second duration of utilization (ΔT′) becomes less than a second predetermined threshold.

8. An aircraft comprising:
a power plant having at least one engine, the engine operating within a performance envelope covering at least a first rating and a second rating, the first rating presenting a first power (P1) which the engine can develop over a predetermined first time interval (D1), the second rating presenting a second power (P2) greater than the first power (P1) which the engine can develop continuously over a predetermined second time interval (D2) shorter in duration than the first time interval, the engine operating to develop a third power (P3) greater than the first power (P1) and less than the second power (P2);
a processor for determining, while the engine is developing the third power (P3), a potential first duration of utilization (ΔT) of the engine to develop continuously the second power (P2) which takes into account engine deterioration caused while the engine is developing the third power (P3) relative to engine deterioration which would be caused if the engine developed the second power (P2) instead of the third power (P3) whereby the first duration of utilization (ΔT) is a third time interval longer in duration than the second time interval and shorter in duration than the first time interval;
a display for displaying the first duration of utilization (ΔT) in the form of a countdown which elapses at a speed that is variable and that depends on the third power (P3) relative to the second power (P2) such that a pilot can be apprised from the countdown of a remaining duration that the engine can be operated to develop continuously the second power (P2); and
wherein the processor determining the potential first duration of utilization (ΔT) amounts to creating for the performance envelope a third rating presenting the third power (P3) which the engine can develop continuously over the third time interval with the first rating, the second rating, and time between overhauls (TBO) for which the engine is associated remaining unchanged.

9. The aircraft according to claim 8 , wherein the closer the third power (P3) comes to the second power (P2), the faster the first duration of utilization (ΔT) elapses.

10. The aircraft according to claim 8 , wherein the power plant has two engines and the first duration of utilization (ΔT) is determined for each engine, with the smaller first duration of utilization (ΔT) being displayed.

11. A device for an aircraft power plant having at least one engine operating within a performance envelope covering at least a first rating and a second rating, the first rating presenting a first power (P1) which the engine can develop over a predetermined first time interval (D1), the second rating presenting a second power (P2) greater than the first power (P1) which the engine can develop continuously over a predetermined second time interval (D2) shorter in duration than the first time interval, the device comprising:
a processor for determining, while the engine is developing a third power (P3) greater than the first power (P1) and less than the second power (P2) a potential first duration of utilization (ΔT) of the engine to develop continuously the second power (P2) which takes into account engine deterioration caused while the engine is developing the third power (P3) relative to engine deterioration which would be caused if the engine developed the second power (P2) instead of the third power (P3) whereby the first duration of utilization (ΔT) is a third time interval longer in duration than the second time interval and shorter in duration than the first time interval;
a display for displaying to a pilot the first utilization duration (ΔT) in the form of a countdown which elapses at a variable speed dependent on the third power (P3) relative to the second power (P2) such that when controlling the operation of the engine the pilot can be apprised from the countdown of a remaining duration that the engine can be operated to develop continuously the second power (P2);
a controller for controlling the operation of the engine using information provided by the countdown; and
wherein the processor determining the potential first duration of utilization (ΔT) amounts to creating for the performance envelope a third rating presenting the third power (P3) which the engine can develop continuously over the third time interval with the first rating, the second rati

Assignees

• Airbus Helicopters

Inventors

• Dyrla Frederic

Classifications

• F01D21/14 Primary

  responsive to other specific conditions · CPC title

• F05D2220/329

  in helicopters · CPC title

• F02C3/113 Primary

  with variable power transmission between rotors · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F02C9/00

  Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) · CPC title