Methods and apparatus for model predictive control of aircraft gas turbine engines

US 6,823,253 B2
Filed: 11/27/2002
Issued: 11/23/2004
Est. Priority Date: 11/27/2002
Status: Expired due to Term

First Claim

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1. A method of designing the operations and controls of a aircraft gas turbine engine, said method comprising:

generating an operations model for the gas turbine including at least one objective function;

defining operations and control constraints for the operations model of the gas turbine; and

providing an online dynamic optimizer/controller that dynamically optimizes and controls operation of the aircraft gas turbine engine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation.

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Abstract

A method of designing the operations and controls of a aircraft gas turbine engine includes generating an operations model for the gas turbine include at least one objective function, defining operations and control constraints for the operations model of the gas turbine, and providing an online dynamic optimizer/controller that dynamically optimizes and controls operation of the gas turbine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation.

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20 Claims

1. A method of designing the operations and controls of a aircraft gas turbine engine, said method comprising:
- generating an operations model for the gas turbine including at least one objective function;
  
  defining operations and control constraints for the operations model of the gas turbine; and
  
  providing an online dynamic optimizer/controller that dynamically optimizes and controls operation of the aircraft gas turbine engine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation.
- View Dependent Claims (2, 3, 4, 5, 6, 7)
- - 2. A method according to claim 1, wherein the optimizer/controller performs following steps in a loop:
    - (A) estimating the current engine state and applicable constraints;
      
      (B) for a given control/simulation time period, determining a control action by optimizing an objective function based on the operation model while respecting the applicable constraints;
      
      (C) executing the control action determined in step (B).
  - 3. A method according to claim 1 further comprising defining an objective J in accordance with:
    - $\begin{matrix} J = \sum_{i = 1}^{p} {({Y1}_{i} - {Y1ref}_{i})}^{2} + γ * \sum_{i = 1}^{p} {({Y2}_{i} - {Y2ref}_{i})}^{2} + \\ ρ_{1} * \sum_{i = 1}^{p} Δ U 1_{i}^{2} + ρ_{2} \sum_{i = 1}^{p} Δ U 2_{i}^{2} + \\ δ_{1} \sum_{i = 1}^{p} {(e^{(Out 1_{\min} - Out 1_{i})})}^{2} + δ_{2} \sum_{i = 1}^{p} {(e^{(Out 2_{i} - Out 2_{\max})})}^{2} + \dots . \end{matrix}$
  - 4. A method in accordance with claim 3 further comprising computing a gradient of J.
  - 5. A method in accordance with claim 4 further comprising taking steps in a negative gradient direction until J is minimized.
  - 6. A method in accordance with claim 4 further comprising taking steps in a negative gradient direction until the number of steps equals a predetermined number.
  - 7. A method in accordance with claim 4 further comprising taking steps in a negative gradient direction until an elapsed time exceeds a predetermined time interval.

8. A system for designing the operations and controls of an aircraft gas turbine engine, said system comprising:
- a computing unit with an input unit for generating an operations model for the aircraft gas turbine engine to include at least one objective function and for defining operations and controls constraints for the operations model of the aircraft gas turbine engine; and
  
  a dynamic online optimizer/controller configured to dynamically optimize and control operation of the gas turbine using model predictive control based on the operations model and the operations and control constraints using an Extended Kalman Filter for estimation.
- View Dependent Claims (9, 10, 11, 12, 13)
- - 9. A system according to claim 8, wherein said optimizer/controller is configured to perform the following steps in a loop:
    - (A) estimating the current engine state and applicable constraints;
      
      (B) for a given control/simulation time period, determining a control action by optimizing an objective function based on the operation model while respecting the applicable constraints;
      
      (C) executing the control action determined in step (B).
  - 10. A system in accordance with claim 8 wherein said optimizer/controller is configured to compute the gradient of J wherein:
    - $\begin{matrix} J = \sum_{i = 1}^{p} {({Y1}_{i} - {Y1ref}_{i})}^{2} + γ * \sum_{i = 1}^{p} {({Y2}_{i} - {Y2ref}_{i})}^{2} + \\ ρ_{1} * \sum_{i = 1}^{p} Δ U 1_{i}^{2} + ρ_{2} \sum_{i = 1}^{p} Δ U 2_{i}^{2} + \\ δ_{1} \sum_{i = 1}^{p} {(e^{(Out 1_{\min} - Out 1_{i})})}^{2} + δ_{2} \sum_{i = 1}^{p} {(e^{(Out 2_{i} - Out 2_{\max})})}^{2} + \dots . \end{matrix}$
  - 11. A system in accordance with claim 10 wherein said optimizer/controller is configured to traverse the gradient in a negative direction until a number of steps equals a predetermined number.
  - 12. A system in accordance with claim 10 wherein said optimizer/controller is configured to traverse the gradient in a negative direction until J is minimized.
  - 13. A system in accordance with claim 10 wherein said optimizer/controller is configured to traverse the gradient in a negative direction until an elapsed time exceeds a predetermined time interval.

14. A non-linear model-based control method for controlling propulsion in a aircraft gas turbine engine, the method comprising:
- a) obtaining information about the current state of the engine using an Extended Kalman Filter;
  
  b) updating model data information about the engine in an model-based control system to reflect the current state of the engine;
  
  c) comparing the information about the current state of the engine with the model data information about the engine in the model;
  
  d) determining the optimal corrective action to take given the current state of the engine, the objective function, and the constraints of the engine;
  
  e) outputting a control command to implement the optimal corrective action; and
  
  f) repeating steps a)-e) as necessary to ensure the performance of the engine is optimized at all times.
- View Dependent Claims (15, 16, 17, 18, 19, 20)
- - 15. A method in accordance with claim 14 wherein said obtaining current information comprises defining an objective J in accordance with:
    - $\begin{matrix} J = \sum_{i = 1}^{p} {({Y1}_{i} - {Y1ref}_{i})}^{2} + γ * \sum_{i = 1}^{p} {({Y2}_{i} - {Y2ref}_{i})}^{2} + \\ ρ_{1} * \sum_{i = 1}^{p} Δ U 1_{i}^{2} + ρ_{2} \sum_{i = 1}^{p} Δ U 2_{i}^{2} + \\ δ_{1} \sum_{i = 1}^{p} {(e^{(Out 1_{\min} - Out 1_{i})})}^{2} + δ_{2} \sum_{i = 1}^{p} {(e^{(Out 2_{i} - Out 2_{\max})})}^{2} + \dots . \end{matrix}$
  - 16. A method in accordance with claim 15 further comprising computing a gradient of J.
  - 17. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until J is minimized.
  - 18. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until the number of steps equals a predetermined number.
  - 19. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until an elapsed time exceeds a predetermined time interval.
  - 20. A method in accordance with claim 16 further comprising taking steps in a negative gradient direction until a first to occur of:

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Current Assignee
General Electric Company
Original Assignee
General Electric Company
Inventors
Brunell, Brent Jerome
Primary Examiner(s)
Zanelli, Michael J.

Application Number

US10/306,433
Publication Number

US 20040102890A1
Time in Patent Office

727 Days
Field of Search

701/100, 700/29, 700/30, 700/31
US Class Current

701/100
CPC Class Codes

G05B 13/048 using a predictor

Methods and apparatus for model predictive control of aircraft gas turbine engines

First Claim

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Methods and apparatus for model predictive control of aircraft gas turbine engines

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