System and method for providing in-flight reverse thrust for an aircraft

Patent metadata

Field	Value
Publication number	US-11668253-B2
Application number	US-202017072477-A
Country	US
Kind code	B2
Filing date	Oct 16, 2020
Priority date	Oct 16, 2020
Publication date	Jun 6, 2023
Grant date	Jun 6, 2023

Abstract

A method and a system for providing in-flight reverse thrust for an aircraft are provided. The aircraft comprises an engine having a rotor, a compressor mechanically coupled to the rotor, and a variable geometry mechanism provided upstream of the compressor and configured to modulate an amount of compression work performed by the compressor. The method comprises operating the rotor with the variable geometry mechanism in a first position, receiving a request to increase reverse thrust for the rotor, in response to the request, adjusting the variable geometry mechanism from the first position towards a second position, the variable geometry mechanism having a greater opening angle in the second position than in the first position, and operating the rotor with the variable geometry mechanism in the second position for causing an increase in the amount of compression work performed by the compressor and an increase in reverse thrust for the rotor.

First claim

The invention claimed is:

1. A method for providing in-flight reverse thrust for an aircraft, the aircraft comprising an engine having a rotor, a compressor mechanically coupled to the rotor, and a variable geometry mechanism provided upstream of the compressor and configured to modulate an amount of compression work performed by the compressor, the variable geometry mechanism being separate from the rotor, the method comprising:
operating the rotor with the variable geometry mechanism in a first position;
receiving a request to increase reverse thrust for the rotor with the rotor operating in a windmilling state;
in response to the request, adjusting the variable geometry mechanism from the first position towards a second position, the variable geometry mechanism having a greater opening angle in the second position than in the first position;
operating the rotor with the variable geometry mechanism in the second position for causing an increase in the amount of compression work performed by the compressor and an increase in reverse thrust for the rotor, the rotor being operated with the variable geometry mechanism in the second position for causing a decrease in a rotational speed of the rotor as a result of the increase in the amount of compression work performed by the compressor; and
in response to the decrease in the rotational speed of the rotor, decreasing a pitch angle of the rotor for increasing the rotational speed of the rotor toward a reference speed, the decrease in the pitch angle resulting in the increase in reverse thrust.

2. The method of claim 1 , wherein adjusting the variable geometry mechanism comprises outputting one or more position control signals to one or more actuators coupled to the variable geometry mechanism, the one or more position control signals comprising instructions for the one or more actuators to adjust the variable geometry mechanism to the second position.

3. The method of claim 1 , wherein decreasing the pitch angle of the rotor comprises outputting one or more pitch control signals to a pitch change mechanism coupled to the rotor, the one or more pitch control signals comprising instructions for the pitch change mechanism to decrease the pitch angle of the rotor.

4. The method of claim 1 , wherein adjusting the variable geometry mechanism comprises adjusting one or more variable inlet guide vanes provided upstream of a low pressure compressor of the engine.

5. The method of claim 1 , wherein adjusting the variable geometry mechanism comprises adjusting one or more variable guide vanes provided upstream of a high pressure compressor of the engine.

6. The method of claim 1 , wherein the received request is indicative of a requested amount of reverse thrust increase, the method further comprising determining the second position based on the requested amount of reverse thrust increase.

7. The method of claim 1 , wherein the method comprises operating the rotor comprising a variable pitch propeller.

8. The method of claim 1 , wherein the method comprises operating the rotor comprising a fixed pitch propeller.

9. The method of claim 1 , wherein the method comprises operating the rotor comprising a variable pitch fan.

10. The method of claim 1 , wherein the method comprises operating the rotor comprising a fixed pitch fan.

11. A system for providing in-flight reverse thrust for an aircraft, the aircraft comprising an engine having a rotor, a compressor mechanically coupled to the rotor, and a variable geometry mechanism provided upstream of the compressor and configured to modulate an amount of compression work performed by the compressor, the variable geometry mechanism being separate from the rotor, the system comprising:
at least one processing unit; and
at least one non-transitory computer-readable memory having stored thereon program instructions executable by the processing unit for:
operating the rotor with the variable geometry mechanism in a first position;
receiving a request to increase reverse thrust for the rotor with the rotor operating in a windmilling state;
in response to the request, adjusting the variable geometry mechanism from the first position towards a second position, the variable geometry mechanism having a greater opening angle in the second position than in the first position;
operating the rotor with the variable geometry mechanism in the second position for causing an increase in the amount of compression work performed by the compressor and an increase in reverse thrust for the rotor, the rotor being operated with the variable geometry mechanism in the second position for causing a decrease in a rotational speed of the rotor as a result of the increase in the amount of compression work performed by the compressor; and
in response to the decrease in the rotational speed of the rotor, decreasing a pitch angle of the rotor for increasing the rotational speed of the rotor toward a reference speed, the decrease in the pitch angle resulting in the increase in reverse thrust.

12. The system of claim 11 , wherein the instructions are executable by the processing unit for adjusting the variable geometry mechanism comprising outputting one or more position control signals to one or more actuators coupled to the variable geometry mechanism, the one or more position control signals comprising instructions for the one or more actuators to adjust the variable geometry mechanism to the second position.

13. The system of claim 11 , wherein the instructions are executable by the processing unit for decreasing the pitch angle of the rotor comprising outputting one or more pitch control signals to a pitch change mechanism coupled to the rotor, the one or more pitch control signals comprising instructions for the pitch change mechanism to decrease the pitch angle of the rotor.

14. The system of claim 11 , wherein the instructions are executable by the processing unit for adjusting the variable geometry mechanism comprising adjusting one or more variable inlet guide vanes provided upstream of a low pressure compressor of the engine.

15. The system of claim 11 , wherein the instructions are executable by the processing unit for adjusting the variable geometry mechanism comprising adjusting one or more variable guide vanes provided upstream of a high pressure compressor of the engine.

16. The system of claim 11 , wherein the instructions are executable by the processing unit for receiving the request indicative of a requested amount of reverse thrust increase, the method further comprising determining the second position based on the requested amount of reverse thrust increase.

Assignees

• Pratt & Whitney Canada

Inventors

• Cormier Charles
• Coutu Daniel

Classifications

• F05D2270/024

  to keep rotational speed constant · CPC title

• F02K1/66

  using reversing fan blades · CPC title

• F05D2220/324

  to drive unshrouded, low solidity propeller · CPC title

• F05D2270/051

  Thrust · CPC title

• F05D2270/304

  Spool rotational speed · CPC title