Compact aero-thermo model based control system estimator starting algorithm

Patent metadata

Field	Value
Publication number	US-10480416-B2
Application number	US-201414770388-A
Country	US
Kind code	B2
Filing date	Mar 14, 2014
Priority date	Mar 15, 2013
Publication date	Nov 19, 2019
Grant date	Nov 19, 2019

Abstract

Systems and methods for controlling a fluid based engineering system are disclosed. The systems and methods may include a model processor for generating a model output, the model processor including a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. The model processor may include an input object for processing model input and setting a model operating mode, the model operating mode being a starting mode if the model input is within a data range associated with a starting operation of the control device. The model processor may further include an estimate state module for determining an estimated state of the model based on a prior state model output and the current state model of the open loop model.

First claim

What is claimed is:

1. A control system, comprising:
an actuator for positioning a control surface of a control device;
a control law for directing the actuator as a function of a model output; and
a model processor for generating the model output, the model processor comprising:
an input object for processing a model input vector and setting a model operating mode, the model operating mode being a starting mode if the model input vector comprises a data range associated with a starting operation of the control device;
a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;
wherein the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control device and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;
an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters; and
an output object for processing at least the synthesized parameters of the model to determine the model output.

2. The control system of claim 1 , wherein the data range associated with the starting operation of the control device is values under a threshold idle condition of the control device.

3. The control system of claim 1 , wherein the data range associated with the starting operation of the control device is values under a threshold condition for starting the control device.

4. The control system of claim 1 , wherein the starting mode includes replacement model input values for the values that are outside of the data range associated with the starting operation of the control device.

5. The control system of claim 1 , wherein the input object uses a spool speed value of the model input vector to determine if the model input vector is within a data range associated with a starting operation of the control device.

6. The control system of claim 5 , wherein the starting mode includes replacement values for spool speed values within the data range associated with the starting operation of the control device for replacing spool speed values that are outside of the data range associated with the starting operation of the control device.

7. The control system of claim 1 , wherein the model input vector includes one or more of raw effector data, boundary conditions, engine sensing data, unit conversion information, range limiting information, rate limiting information, dynamic compensation determinations, and synthesized lacking inputs.

8. The control system of claim 1 , wherein the control device is a gas turbine engine.

9. The control system of claim 8 , wherein the one or more cycle synthesis modules are based on one or more mathematical abstractions of physical processes associated with components of a thermodynamic cycle of the gas turbine engine.

10. A method for controlling a control device, the method comprising:
generating a model output using a model processor, the model processor comprising:
an input object for processing a model input vector and setting a model operating mode, the model operating mode being a starting mode if the model input vector comprises a data range associated with a starting operation of the control device;
a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;
wherein the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the control device and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;
an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameter; and
an output object for processing at least the synthesized parameters of the model to determine the model output;
directing an actuator associated with the control device as a function of a model output using a control law; and
positioning a control surface of the control device using the actuator.

11. The method of claim 10 , wherein the data range associated with the starting operation of the control device is values under a threshold idle condition of the control device.

12. The method of claim 10 , wherein the data range associated with the starting operation of the control device is values under a threshold condition for starting the control device.

13. The method of claim 10 , wherein the starting mode includes replacement model input values for the values that are outside of the data range associated with the starting operation of the control device.

14. The method of claim 10 , wherein the input object uses a spool speed value of the model input vector to determine if the model input vector comprises a data range associated with a starting operation of the control device.

15. The method of claim 14 , wherein the starting mode includes replacement values for spool speed values within the data range associated with the starting operation of the control device for replacing spool speed values that are outside of the data range associated with the starting operation of the control device.

16. A gas turbine engine comprising:
a fan;
a compressor section downstream of the fan;
a combustor section downstream of the compressor section;
an actuator for positioning a control surface of an element of the gas turbine engine;
a control law for directing the actuator as a function of a model output;
a model processor for generating the model output, the model processor comprising:
an input object for processing a model input vector and setting a model operating mode, the model operating mode being a starting mode if the model input vector comprises a data range associated with a starting operation of the gas turbine engine;
a set state module for setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode;
wherein the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and the model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules, each member of the series of cycle synthesis modules modeling a component of a cycle of the gas turbine engine and comprising a series of utilities, the utilities based on mathematical abstractions of physical laws that govern behavior of the component;
an estimate state module for determining an estimated state of the model based on at least one of a prior state, the current state derivatives, the solver state errors, and the synthesized parameters; and
an output object for pro

Assignees

• United Technologies Corp

Inventors

• Karpman Boris
• Meisner Richard P
• Sembiante David
• Niemczycki Thomas

Classifications

• F04D29/321

  for axial flow compressors · CPC title

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title

• G05D7/0629

  characterised by the type of regulator means · CPC title

• F05D2260/81

  Modelling or simulation · CPC title

• G05B13/04

  involving the use of models or simulators · CPC title