DISTRIBUTED APPROACH TO ELECTRONIC ENGINE CONTROL FOR GAS TURBINE ENGINES

• US 20100274416A1
• Filed: 04/22/2009
• Published: 10/28/2010
• Est. Priority Date: 04/22/2009
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Poisson, Richard A.
• Granted Patent: US 8,295,995 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64D 31/14 Transmitting means between initiating means and power plants
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: G05B 19/42 Recording and playback systems, i.e. in which the programme is recorded from a cycle of operations, e.g. the cycle of operations being manually controlled, after which this record is played back on the same machine
• CPC Class Codes: G05B 2219/25232 DCS, distributed control system, decentralised control unit
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A distributed electronic engine control system includes an airframe module, an electronic engine control module, and an engine I/O module. The modules are arranged in locations remote from one another. A serial communications bus interconnects the modules with one another. A first engine controls device is connected to the engine I/O module and is configured to interact with an engine component and provide a first data. The engine I/O module includes inner loop control logic that uses the first data and produces a second data in response thereto. The electronic engine control module includes an outer loop control logic using the second data and produces a third data in response thereto. The airframe module receives power and distributes the power to the electronic engine control and engine I/O modules. The first, second and third data are provided on the serial communications bus.

Claims

1. A distributed electronic engine control system comprising:

an airframe module, an electronic engine control module, and an engine I/O module, the modules arranged in locations remote from one another, each of the modules removably secured to a docking station at each of the locations;

a serial communications bus interconnecting the modules with one another;

a first engine controls device connected to the engine I/O module and configured to interact with an engine component and provide a first data; and

wherein the engine I/O module includes inner loop control logic using the first data and producing a second data in response thereto, the electronic engine control module including an outer loop control logic using the second data and producing a third data in response thereto, the airframe module receiving power and distributing the power to the electronic engine control and engine I/O modules, the first, second and third data provided on the serial communications bus.

2. The system according to claim 1, comprising an engine including the engine component and the engine controls device, wherein the engine comprises a fan case surrounding a core, the engine I/O mounted on the core.

3. The system according to claim 2, wherein the electronic engine control module is mounted on one of the core and the fan case.

4. The system according to claim 2, wherein the airframe module is mounted on one of the fan case and an airframe.

5. The system according to claim 1, wherein the modules are line replaceable units, each line replaceable unit including the docking station, one of the modules, an electrical connection interconnecting the module to its respective docking station, and a latching feature removably securing the module to its respective docking station.

6. The system according to claim 1, wherein the serial communications bus is serial message-based with the data arriving and departing on the serial communications bus at known times.

7. The system according to claim 1, wherein the first engine controls device includes one of a sensor and an actuator, the sensor configured to sense information relating to the engine component, and the actuator configured to actuate the engine component between multiple positions.

8. The system according to claim 7, wherein the first engine control device includes at least one of a variable stator vane actuator, a fuel metering valve, a temperature sensor, a pressure sensor, and a position sensor.

9. The system according to claim 1, wherein the inner loop control logic is programmed to perform at least one of shaping the first data to produce the second data, filtering the first data to produce the second data and receiving the first data to produce a command corresponding to the second data, the command provided to the first engine control device.

10. The system according to claim 1, wherein the outer loop control logic includes engine control laws, the third data corresponding to a command signal provided to the engine I/O module.

11. The system according to claim 9, wherein the inner loop control logic corresponds to engine overspeed processing.

12. The system according to claim 1, wherein the airframe module includes power conditioning logic for the power and a permanent magnet alternator interface.

13. The system according to claim 1, wherein the airframe module includes thrust reverser control logic.

14. The system according to claim 1, comprising a second engine controls device connected to the airframe control module and configured to interact with another engine component and provide a fourth data.

15. The system according to claim 1, comprising a prognostics and health monitoring module arranged in another location remote from the other locations, the prognostics and health monitoring module removably secured to a docking station at its respective location and interconnected to the serial communications bus, the prognostics and health monitoring module including data reduction algorithms and data storage corresponding to prognostics and health information relating to an engine component.

16. The system according to claim 15, comprising a download device, the prognostics and health monitoring module configured to communicate with the download device to provide a fifth data from the data storage.

17. A method of controlling a gas turbine engine comprising:

a) receiving data in an engine I/O module from at least one of a engine sensor and an engine effector;

b) manipulating the first data with an inner loop control logic residing in the engine I/O module to produce a second data;

c) broadcasting the first and second data over a serial communications bus;

d) receiving the second data from the serial communications bus in an electronic engine control module located remotely from the engine I/O module, the electronic engine control module including an outer loop control logic;

e) manipulating the second data with the outer control loop logic to produce a third data corresponding to a command signal;

f) broadcasting the command signal over the serial communications bus; and

g) receiving the command signal from the serial communications bus in the engine I/O module and commanding an engine controls device based upon the command signal.

18. The method according to claim 17, wherein the gas turbine engine includes a fan case surrounding a core, the engine I/O module removably mounted on the core and the electronic engine control module removably mounted on the fan case.

19. The method according to claim 17, comprising the step of h) monitoring a health of an engine component in a prognostics and health monitoring module based upon the data received from the communications bus, the prognostics and health monitoring module located remotely from the electronic engine control and engine I/O modules.

20. A distributed electronic engine control system comprising:

an airframe module, an electronic engine control module, and an engine I/O module, the modules discrete from one another and arranged in locations remote from one another;

a communications bus interconnecting the modules with one another;

a first engine controls device connected to the engine I/O module and configured to interact with an engine component and provide a first data; and

wherein the engine I/O module includes inner loop control logic using the first data and producing a second data in response thereto, the electronic engine control module including an outer loop control logic using the second data and producing a third data in response thereto, the airframe module providing power conditioning, the first, second and third data provided on the serial communications bus.