Systems and Methods Involving Multiplexed Engine Control Signals

• US 20090292437A1
• Filed: 05/22/2008
• Published: 11/26/2009
• Est. Priority Date: 05/22/2008
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cloft, Thomas G.
• Granted Patent: US 8,140,242 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F01D 17/20 Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted sensing elements alone F01D17/02; final actuators alone F01D17/10
• 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: F05D 2270/54 by electronic means, e.g. electronic tubes, transistors or IC's within an electronic circuit
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Systems and methods involving multiplexed engine control signals are provided. In this regard, a representative engine control system for a gas turbine engine includes: a signal relay device operative to receive multiplexed signals from an engine electronic control (EEC), demultiplex the signals, and provide demultiplexed signals to corresponding ones of multiple control devices of the engine.

Claims

1. A gas turbine engine system comprising:

an engine electronic control (EEC) operative to receive and provide information corresponding to engine operating parameters such that a gas turbine engine operates in accordance with the information provided from the EEC;

multiple control devices, each of the control devices being operative to perform at least one of;

monitoring at least one engine operating parameter, providing information corresponding to the at least one engine operating parameter for use by the EEC, and affecting at least one engine operating parameter; and

a signal relay device operative to receive multiplexed signals from the EEC, demultiplex the signals, and provide demultiplexed signals to corresponding ones of the multiple control devices.

2. The system of claim 1, further comprising:

a wiring harness operative to interconnect the EEC and a first of the multiple control devices such that the wiring harness facilitates communication of signals between the EEC and the first of the multiple control devices instead of the signal relay device.

3. The system of claim 2, wherein the first of the multiple control devices is a flight critical device requiring separation of redundant signals for flight certification.

4. The system of claim 2, wherein the first of the multiple control devices is a fuel monitoring unit.

5. The system of claim 1, wherein at least two of the multiple control devices receive demultiplexed signals from the signal relay device.

6. The system of claim 5, wherein the at least two of the multiple control devices are non-flight critical control devices such that separation of redundant signals for each of the at least two of the multiple control devices is not required for flight certification.

7. The system of claim 1, wherein at least one of the multiple control devices is configured to be positioned within a core compartment located in a vicinity of a compressor section of a gas turbine engine.

8. The system of claim 7, wherein at least one of the multiple control devices comprises a turbine cooling air modulating valve configured to be positioned in the core compartment.

9. The system of claim 7, wherein the signal relay device is configured to be positioned within the core compartment.

10. The system of claim 9, further comprising a multiplex signal wire interconnecting the signal relay device and the EEC.

11. The system of claim 1, wherein the signal relay device is further operative to receive information from the multiple control devices, multiplex the information and provide multiplexed signals containing the information to the EEC.

12. An engine control system for a gas turbine engine having multiple control devices, said engine control system comprising:

a signal relay device operative to receive multiplexed signals from an engine electronic control (EEC), demultiplex the signals, and provide demultiplexed signals to corresponding ones of the multiple control devices.

13. The system of claim 12, wherein the signal relay device is further operative to receive information from the multiple control devices, multiplex the information and provide multiplexed signals containing the information to the EEC.

14. The system of claim 12, further comprising:

a multiplex signal wire operative to interconnect the signal relay device and the EEC; and

non-multiplexed signal wires, each of the non-multiplexed signal wires operative to interconnect the signal relay device and a corresponding one of the multiple control devices.

15. The system of claim 12, further comprising the EEC, the EEC being operative to receive and provide information corresponding to engine operating parameters such that the gas turbine engine operates in accordance with the information provided from the EEC.

16. A method for controlling a gas turbine engine having multiple control devices, said method comprising:

multiplexing, at a first location, engine control signals corresponding to the multiple engine control devices;

demultiplexing the multiplexed engine control signals at second location; and

providing each of the demultiplexed engine control signals to a corresponding one of the multiple control devices.

17. The method of claim 16, wherein:

the multiplexed engine control signals correspond to non-flight critical ones of the multiple control devices; and

the method further comprises providing discrete, non-multiplexed/demultiplexed, control signals to flight critical ones of the multiple control devices.

18. The method of claim 16, further comprising multiplexing information provided by at least two of the multiple control devices such that the information is available for use in controlling operating parameters of the engine.

19. The method of claim 16, wherein the multiplexing is performed by an engine electronic control (EEC).

20. The method of claim 16, wherein the engine is a turbofan gas turbine engine.