Engine and propeller control system

Patent metadata

Field	Value
Publication number	US-2022333535-A1
Application number	US-202217854245-A
Country	US
Kind code	A1
Filing date	Jun 30, 2022
Priority date	Nov 23, 2018
Publication date	Oct 20, 2022
Grant date	—

Abstract

An electronic controller for an engine and a propeller, a control system and related methods are described herein. The control system comprises the controller having a first channel and a second channel independent from and redundant to the first channel. Each channel comprises a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command and at least one propeller control command. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command and at least one propeller protection command. The control system comprises sensors for measuring the parameters of the engine and/or the propeller and effectors configured to control the engine and the propeller.

First claim

What is claimed is:

1 . A control system for an engine and propeller assembly comprising an engine and a propeller coupled to the engine, the system comprising:
at least one first sensor for measuring a first operating parameter of the assembly and at least one second sensor for measuring a second operating parameter of the assembly; at least one control effector configured to control the assembly in a normal mode of operation thereof; at least one protection effector configured to control the assembly to prevent against a hazardous mode of operation thereof; and a controller communicatively coupled to the at least one first sensor, the at least one second sensor, the at least one control effector, and the at least one protection effector, the controller comprising a first communication channel and a second communication channel independent from and redundant to the first channel, each communication channel having a control processor and a protection processor communicating thereover, the control processor controlling the engine and the propeller in the normal mode of operation thereof and the protection processor controlling the engine and the propeller to prevent against the hazardous mode of operation thereof.

2 . The control system of claim 1 , wherein the control processor is configured to receive a first set of engine and propeller parameters comprising the first operating parameter of the assembly from the at least one first sensor, to output, based on the first set of engine and propeller parameters, at least one engine control command and at least one propeller control command to the at least one control effector.

3 . The control system of claim 2 , wherein the at least one engine control command comprises instructions for controlling the engine in the normal mode of operation and the at least one propeller control command comprising instructions for controlling the propeller in the normal mode of operation.

4 . The control system of claim 2 , wherein the protection processor is configured to receive a second set of engine and propeller parameters comprising the second operating parameter of the assembly from the at least one second sensor, to output, based on the second set of engine and propeller parameters, at least one engine protection command and at least one propeller protection command to the at least one protection effector.

5 . The control system of claim 4 , wherein the at least one engine protection command comprises instructions overriding the at least one engine control command to prevent hazardous operation of the engine and the at least one propeller protection command comprising instructions overriding the at least one propeller control command to prevent hazardous operation of the propeller.

6 . The control system of claim 1 , wherein each of the at least one first sensor and the at least one second sensor comprises a first coil and a second coil, the first operating parameter measured via the first coil and the second coil of the at least one first sensor and the second operating parameter measured via the first coil and the second coil of the at least one second sensor.

7 . The control system of claim 6 , wherein the first coil of the at least one first sensor provides a first measurement of the first operating parameter to the control processor of the first communication channel and the second coil of the at least one first sensor provides a second measurement of the first operating parameter to the control processor of the second communication channel, the second measurement of the first operating parameter independent from and redundant to the first measurement of the first operating parameter.

8 . The control system of claim 7 , wherein the first operating parameter is an engine parameter and wherein the control processor of the first communication channel is configured to generate the at least one engine control command based on the first measurement of the first operating parameter and the control processor of the second communication channel is configured to generate the at least one engine control command based on the second measurement of the first operating parameter.

9 . The control system of claim 7 , wherein the first operating parameter is a propeller parameter and wherein the control processor of the first communication channel is configured to generate the at least one propeller control command based on the first measurement of the first operating parameter and the control processor of the second communication channel is configured to generate the at least one propeller control command based on the second measurement of the first operating parameter.

10 . The control system of claim 7 , wherein the at least one first sensor is coupled to a gear box of the engine for measuring power turbine speed of the engine, and the control processor is configured to determine propeller rotational speed based on the power turbine speed.

11 . The control system of claim 7 , wherein the at least one first sensor is a torque sensor for measuring torque of the engine and the control processor is configured to determine shaft horse power based on the torque of the engine.

12 . The control system of claim 7 , wherein the first coil of the at least one second sensor provides a first measurement of the second operating parameter to the protection processor of the first communication channel and the second coil of the at least one second sensor provides a second measurement of the second operating parameter to the protection processor of the second communication channel, the second measurement of the second operating parameter independent from and redundant to the first measurement of the second operating parameter.

13 . The control system of claim 12 , wherein the second operating parameter is an engine parameter and wherein the protection processor of the first communication channel is configured to generate the at least one engine protection command based on the first measurement of the second operating parameter and the protection processor of the second communication channel is configured to generate the at least one engine protection command based on the second measurement of the second operating parameter.

14 . The control system of claim 12 , wherein the second operating parameter is a propeller parameter and wherein the protection processor of the first communication channel is configured to generate the at least one propeller protection command based on the first measurement of the second operating parameter and the protection processor of the second communication channel is configured to generate the at least one propeller protection command based on the second measurement of the second operating parameter.

15 . The control system of claim 1 , wherein the at least one control effector comprises a first control effector comprising a first control actuator to control at least one physical component of the engine and a second control actuator to control at least one physical component of the propeller, the first control actuator configured to receive the at least one engine control command from the control processor of the first communication channel and the second control actuator configured to receive the at least one propeller control command from the control processor of the first communication channel.

16 . The control system of claim 15 , wherein the at least one control effector further comprises a second control effector comprising a first control actuator to control the at least one physical component of the engine and a second control actuator to

Assignees

• Pratt & Whitney Canada

Inventors

• Chahal Jasraj
• Duke Brant
• Lisio Carmine
• Jarvo Jim R
• Zingaro Giancarlo

Classifications

• B64C11/305

  characterised by being influenced by other control systems, e.g. fuel supply · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D31/00

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• F02C9/58 Primary

  with control of a variable-pitch propeller · CPC title

• F05D2220/325

  to drive unshrouded, high solidity propeller · CPC title