Distributed gas turbine engine control system with remote interface units

• US 9,388,744 B2
• Filed: 03/30/2012
• Issued: 07/12/2016
• Est. Priority Date: 03/30/2012
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Mathews, Harry Kirk Jr., Brunell, Brent Jerome, Lis, Simon Shlomo, Carpenter, R. Sheldon, Dasgupta, Samhita, Adibhatla, Sridhar, Waun, Scott Douglas, Andarawis, Emad Andarawis
• Primary Examiner(s): Rivera, Carlos A
• Application Number:
  US13/436,184
• Publication Number:
  US 20130255220A1
• Time in Patent Office: 1,565 Days
• US Class Current: 1/1
• CPC Class Codes: F02C 9/00 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 Class Codes: F05D 2270/46 redundant, i.e. failsafe operation
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

In one embodiment, a gas turbine engine control system includes an engine controller configured to control multiple parameters associated with operation of a gas turbine engine system. The gas turbine engine control system also includes multiple remote interface units communicatively coupled to the engine controller. The remote interface unit is configured to receive an input signal from the engine controller indicative of respective target values of at least one parameter, and the remote interface unit is configured to provide closed-loop control of the at least one parameter based on the input signal and feedback signals indicative of respective measured values of the at least one parameter.

Claims

1. A gas turbine engine control system, comprising:

an engine controller configured to control a plurality of parameters associated with operation of a gas turbine engine system; and

a plurality of remote interface units communicatively coupled to the engine controller, wherein each remote interface unit is configured to receive an input signal from the engine controller indicative of respective target values of at least one parameter of the plurality of parameters, and each remote interface unit is configured to provide closed-loop control of the at least one parameter based on the input signal and feedback signals indicative of respective measured values of the at least one parameter, wherein the plurality of remote interface units are distributed throughout the gas turbine engine at a compressor, a combustor, and a turbine, wherein at least one remote interface unit comprises a plurality of local loop closure modules, and each local loop closure module is configured to independently provide closed-loop control of a respective parameter of the plurality of parameters.

2. The gas turbine engine control system of claim 1, wherein each remote interface unit comprises an actuator configured to adjust the at least one parameter, and a sensor configured to output the feedback signals.

3. The gas turbine engine control system of claim 1, wherein each local loop closure module is configured to provide the closed-loop control of a respective parameter by instructing an actuator to adjust the respective parameter based on the feedback signals indicative of the respective measured values from a sensor.

4. The gas turbine engine control system of claim 1, wherein at least two of the plurality of local loop closure modules are configured to provide redundant closed-loop control of the at least one parameter.

5. The gas turbine engine control system of claim 1, wherein at least one remote interface unit of the plurality of remote interface units comprises a smart actuator assembly having an actuator configured to adjust the at least one parameter, a sensor configured to output the feedback signals, and a respective interface controller communicatively coupled to the actuator and to the sensor, wherein the interface controller is configured to provide the closed-loop control of the at least one parameter.

6. The gas turbine engine control system of claim 1, wherein each remote interface unit comprises a communication module configured to receive the input signal from the engine controller.

7. The gas turbine engine control system of claim 1, wherein the engine controller comprises an engine control module configured to control the plurality of parameters, and a power conditioning module configured to provide electrical power to the engine control module and to the plurality of remote interface units, wherein the engine control module and the power conditioning module are disposed within independent housings positioned remote from one another.