Operating a turboprop engine for in-flight restart

Patent metadata

Field	Value
Publication number	US-11719167-B2
Application number	US-202117220008-A
Country	US
Kind code	B2
Filing date	Apr 1, 2021
Priority date	Apr 1, 2021
Publication date	Aug 8, 2023
Grant date	Aug 8, 2023

Abstract

There are described methods and systems for operating an aircraft turboprop engine. The method comprises controlling a propeller of the turboprop engine based on a selected one of a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running; detecting an inflight restart of the turboprop engine; and controlling the propeller during the inflight restart in accordance with at least one of a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle during the inflight restart.

First claim

The invention claimed is:

1. A method for operating an aircraft turboprop engine, the method comprising:
controlling a propeller of the turboprop engine based on a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running;
detecting an inflight restart of the turboprop engine, the detecting of the inflight restart comprising detecting an engine start, and in response to detecting the engine start, detecting the inflight restart using flight conditions; and
controlling the propeller during the inflight restart in accordance with a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle and a decreased reference propeller rotational speed during the inflight restart.

2. The method of claim 1 , wherein the detecting of the inflight restart comprises detecting an engine start and treating the engine start as the inflight restart.

3. The method of claim 1 , wherein the detecting of the inflight restart comprises distinguishing between a normal engine operating state and an inflight restart engine state using the flight conditions, an engine state, and a power lever request.

4. The method of claim 1 , wherein the modified minimum propeller blade angle is a dedicated blade angle schedule for inflight restarts.

5. The method of claim 1 , wherein the modified reference propeller rotational speed is a dedicated propeller rotational speed schedule for inflight restarts.

6. The method of claim 1 , wherein the modified minimum propeller blade angle is the minimum propeller blade angle with an applied bias or an applied gain.

7. The method of claim 1 , wherein the modified reference propeller rotational speed is the reference propeller rotational speed with an applied bias or an applied gain.

8. The method of claim 1 , wherein the detecting of the inflight restart comprises detecting an engine start state and detecting that the aircraft is operating within a range of aircraft speeds.

9. A system for operating an aircraft turboprop engine, the system comprising:
a processor; and
a non-transitory computer-readable medium having stored thereon program instructions executable by the processor for:
controlling a propeller of the turboprop engine based on a reference propeller rotational speed and a minimum propeller blade angle;
detecting an inflight restart of the turboprop engine, the detecting of the inflight restart comprising detecting an engine start, and in response to detecting the engine start, detecting the inflight restart using flight conditions; and
controlling the propeller during the inflight restart in accordance with a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle and a decreased reference propeller rotational speed during the inflight restart.

10. The system of claim 9 , wherein the detecting of the inflight restart comprises detecting an engine start and treating the engine start as the inflight restart.

11. The system of claim 9 , wherein the detecting of the inflight restart comprises distinguishing between a normal engine operating state and an inflight restart engine state using the flight conditions, an engine state, and a power lever request.

12. The system of claim 9 , wherein the modified minimum propeller blade angle is a dedicated blade angle schedule for inflight restarts.

13. The system of claim 9 , wherein the modified reference propeller rotational speed is a dedicated propeller rotational speed schedule for inflight restarts.

14. The system of claim 9 , wherein the modified minimum propeller blade angle is the minimum propeller blade angle with an applied bias or an applied gain.

15. The system of claim 9 , wherein the modified reference propeller rotational speed is the reference propeller rotational speed with an applied bias or an applied gain.

16. The system of claim 9 , wherein the detecting of the inflight restart comprises detecting an engine start state and detecting that the aircraft is operating within a range of aircraft speeds.

17. The system of claim 9 , wherein the detecting of the inflight restart comprises detecting an engine start state and detecting that the aircraft is operating at an altitude greater than a threshold.

18. A method for operating an aircraft turboprop engine, the method comprising:
controlling a propeller of the turboprop engine based on a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running;
when an inflight restart of the turboprop engine is detected, the detecting of the inflight restart comprising detecting an engine start, and in response to detecting the engine start, detecting the inflight restart using flight conditions, increasing the minimum propeller blade angle above an aerodynamic disking angle and lowering the reference propeller rotational speed used to control the propeller; and
controlling the propeller during the inflight restart with the minimum propeller blade angle as increased and the reference propeller rotational speed as decreased.

19. The method of claim 18 , wherein the increasing of the minimum propeller blade angle comprises increasing the minimum propeller blade angle to a value greater than or equal to an aerodynamic disking angle of the propeller.

20. The method of claim 1 , wherein the detecting of the inflight restart comprises detecting an engine start state and detecting that the aircraft is operating at an altitude greater than a threshold.

Assignees

• Pratt & Whitney Canada

Inventors

• Lopez Simon
• Hebert Jeremie

Classifications

• F02C9/16 Primary

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title

• B64C11/30

  Blade pitch-changing mechanisms · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F05D2270/021

  to prevent overspeed · CPC title

• F02C9/00 Primary

  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