System and method for testing engine performance in-flight

Patent metadata

Field	Value
Publication number	US-11427353-B2
Application number	US-201916713273-A
Country	US
Kind code	B2
Filing date	Dec 13, 2019
Priority date	Dec 13, 2019
Publication date	Aug 30, 2022
Grant date	Aug 30, 2022

Abstract

Systems and Methods are described for testing engine performance in-flight in an aircraft having a first engine and a second engine. The method comprises operating the first engine at a first power level in an output speed governing mode, operating the second engine at a second power level greater than the first power level in a core speed governing mode concurrently with the first engine operating at the first power level in the output speed governing mode, and performing an engine performance test on the second engine while the second engine is at the second power level in the core speed governing mode.

First claim

The invention claimed is:

1. A method for testing engine performance in-flight in a rotary-wing aircraft having a first engine and a second engine both drivingly engaged to a rotary wing of the rotary-wing aircraft, the method comprising:
operating the first engine at a first power level in an output speed governing mode to govern a speed of the rotary wing;
operating the second engine at a second power level greater than the first power level in a core speed governing mode to govern a speed of a core of the second engine, the second engine being operated at the second power level in the core speed governing mode concurrently with the first engine operating at the first power level in the output speed governing mode; and
performing an engine performance test on the second engine while the second engine is operating at the second power level in the core speed governing mode and while the first engine is operating at the first power level in the output speed governing mode.

2. The method of claim 1 , wherein operating the first engine at the first power level and operating the second engine at the second power level comprises decreasing the first engine to the first power level and decreasing the second engine to the second power level.

3. The method of claim 1 , further comprising transitioning the first engine and the second engine to an asymmetric operating regime after the engine performance test, wherein the asymmetric operating regime comprises having the second engine in an active mode to provide motive power to the rotary wing and the first engine in a standby mode to provide substantially no motive power to the rotary wing.

4. The method of claim 1 , wherein operating the first engine at the first power level and operating the second engine at the second power level comprises transitioning the first engine and the second engine out of an asymmetric operating regime where the second engine is in an active mode to provide motive power to the rotary wing and the first engine is in a standby mode to provide substantially no motive power to the rotary wing.

5. The method of claim 4 , wherein transitioning out of the asymmetric operating regime comprises increasing the first engine to the first power level and decreasing the second engine to the second power level.

6. The method of claim 1 , wherein operating the first engine at the first power level and operating the second engine at the second power level comprises decreasing the first engine to the first power level and increasing the second engine to the second power level.

7. The method of claim 1 , wherein the method is performed at planned intervals throughout a flight of the rotary-wing aircraft.

8. The method of claim 1 , further comprising transitioning the first engine and the second engine to a stable cruise power level after the engine performance test.

9. The method of claim 1 , further comprising:
determining operating conditions of the rotary-wing aircraft after the engine performance test; and
operating the first engine and the second engine as a function of the operating conditions.

10. A system for testing engine performance in-flight in a rotary-wing aircraft having a first engine and a second engine both drivingly engaged to a rotary wing of the rotary-wing aircraft, the system comprising:
a processing unit; and
a non-transitory computer readable medium having stored thereon program code executable by the processing unit for:
operating the first engine at a first power level in an output speed governing mode to govern a speed of the rotary wing;
operating the second engine at a second power level greater than the first power level in a core speed governing mode to govern a speed of a core of the second engine, the second engine being operated at the second power level in the core speed governing mode concurrently with the first engine operating at the first power level in the output speed governing mode; and
performing an engine performance test on the second engine while the second engine is operating at the second power level in the core speed governing mode and while the first engine is operating at the first power level in the output speed governing mode.

11. The system of claim 10 , wherein operating the first engine at the first power level and operating the second engine at the second power level comprises decreasing the first engine to the first power level and decreasing the second engine to the second power level.

12. The system of claim 10 , wherein the program code is further executable for transitioning the first engine and the second engine to an asymmetric operating regime after the engine performance test, wherein the asymmetric operating regime comprises having the second engine in an active mode to provide motive power to rotary wing and the first engine in a standby mode to provide substantially no motive power to the rotary wing.

13. The system of claim 10 , wherein operating the first engine at the first power level and operating the second engine at the second power level comprises transitioning the first engine and the second engine out of an asymmetric operating regime where the second engine is in an active mode to provide motive power to the rotary wing and the first engine is in a standby mode to provide substantially no motive power to the rotary wing.

14. The system of claim 13 , wherein transitioning out of the asymmetric operating regime comprises increasing the first engine to the first power level and decreasing the second engine to the second power level.

15. The system of claim 10 , wherein operating the first engine at the first power level and operating the second engine at the second power level comprises decreasing the first engine to the first power level and increasing the second engine to the second power level.

16. The system of claim 10 , wherein the engine performance test is repeated at planned intervals throughout a flight of the rotary-wing aircraft.

17. The system of claim 10 , wherein the program code is further executable for transitioning the first engine and the second engine to a stable cruise power level after the engine performance test.

18. The system of claim 10 , wherein the program code is further executable for:
determining operating conditions of the rotary-wing aircraft after the engine performance test; and
operating the first engine and the second engine as a function of the operating conditions.

19. A non-transitory computer readable medium having stored thereon program instructions executable by a processing unit for testing engine performance in-flight in a rotary-wing aircraft having a first engine and a second engine both drivingly engaged to a rotary wing of the rotary-wing aircraft, the program instructions configured for:
operating the first engine at a first power level in an output speed governing mode to govern a speed of the rotary wing;
operating the second engine at a second power level greater than the first power level in a core speed governing mode concurrently with the first engine operating at the first power level in the output speed governing mode to govern a speed of a core of the second engine, the second engine being operated at the second power level in the core speed governing mode; and
performing an engine performance test on the second engine while the second engine is operating at the second power level in the core speed governing mode and while the first engine is operating at the first power level in the output speed governing mode.

Assignees

• Pratt & Whitney Canada

Inventors

• Drolet Martin
• Manoukian Patrick
• Faty Zachary Mounir

Classifications

• F05D2260/80

  Diagnostics · CPC title

• F02C9/42 Primary

  specially adapted for the control of two or more plants simultaneously · CPC title

• F05D2270/13

  to control two or more engines simultaneously · 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

• F05D2220/329

  in helicopters · CPC title