Compact aero-thermo model based control system

Patent metadata

Field	Value
Publication number	US-10767563-B2
Application number	US-201816203995-A
Country	US
Kind code	B2
Filing date	Nov 29, 2018
Priority date	Mar 15, 2013
Publication date	Sep 8, 2020
Grant date	Sep 8, 2020

Abstract

Systems and methods for controlling a fluid-based 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, the dynamic states input to an open loop model based on the model operating mode, where the open loop model generates current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector. A constraint on the state derivatives and solver state errors is based a series of utilities that are based on mathematical abstractions of physical laws that govern behavior of the component. The model processor may include 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.

First claim

What is claimed is:

1. A control system, comprising:
an actuator configured to position a control device comprising a control surface; and
a computer processor configured to execute a control law to control the actuator as a function of a model output and generate the model output based on execution of a plurality of executable instructions:
set a plurality of dynamic states as input to an open loop model based on a model operating mode, the dynamic states comprising a plurality of dynamically determined physics states of a plurality of components of the control device;
generate a plurality of current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector in the open loop model, wherein a constraint on the current state derivatives, solver state errors, and synthesized parameters is based on a series of cycle synthesis modules that model a cycle of the control device, the cycle synthesis modules partitioned into at least a primary stream group and a secondary stream group corresponding to a primary stream and a secondary stream of the components of the control device;
determine an estimated state of the model based on at least one of a prior state and the current state derivatives, the solver state errors, and the synthesized parameters; and
determine the model output based at least in part on the synthesized parameters.

2. The control system of claim 1 , further comprising an operator interface to provide instructions to at least one of the model or the control law.

3. The control system of claim 1 , further comprising system sensors to contribute data to the model input vector.

4. The control system of claim 1 , wherein the cycle synthesis modules comprise at least one configurable utility comprising one or more sub-utilities.

5. The control system of claim 4 , wherein at least one configurable utility is designed to model physical processes of a compressor element.

6. The control system of claim 4 , wherein at least one configurable utility is designed to model physical processes of a turbine element.

7. The control system of claim 1 , wherein the model input vector includes at least one 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, by a computer processor, a model output;
setting a plurality of dynamic states as input to an open loop model based on a model operating mode, the dynamic states comprising a plurality of dynamically determined physics states of a plurality of components of the control device;
generating a plurality of current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector, wherein a constraint on the current state derivatives and solver state errors is based on a series of cycle synthesis modules a cycle of the control device, the cycle synthesis modules partitioned into at least a primary stream group and a secondary stream group corresponding to a primary stream and a secondary stream of the components of the control device;
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;
determining the model output based at least in part on the synthesized parameters;
directing an actuator associated with the control device as a function of the model output using a control law; and
positioning the control device comprising a control surface using the actuator, wherein the actuator positions the control surface.

11. The method of claim 10 , further comprising receiving instructions by the model via an operator interface operatively associated with the control device.

12. The method of claim 10 , wherein the control device is a gas turbine engine.

13. The method of claim 12 , wherein the model is an engine parameter on-board synthesizer.

14. The method of claim 12 , wherein the one or more cycle synthesis modules are based on one or more mathematical abstractions of physical processes associated a thermodynamic cycle of the gas turbine engine.

15. The method of claim 10 , wherein the cycle synthesis modules comprise at least one of configurable utility comprising one or more sub-utilities.

16. A gas turbine engine comprising:
an actuator for positioning the gas turbine engine, wherein the actuator positions a control surface of an element of the gas turbine engine; and
a computer processor configured to execute a control law to control the actuator as a function of a model output and generate the model output based on execution of a plurality of executable instructions to:
set a plurality of dynamic states as input to an open loop model based on a model operating mode, the dynamic states comprising a plurality of dynamically determined physics states of a plurality of components of the control device;
generate a plurality of current state derivatives, solver state errors, and synthesized parameters as a function of the dynamic states and a model input vector in the open loop model, wherein a constraint on the current state derivatives and solver state errors based on a series of cycle synthesis modules that model a cycle of the gas turbine engine, the cycle synthesis modules partitioned into at least a primary stream group and a secondary stream group corresponding to a primary stream and a secondary stream of the components of the control device;
determine 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
determine the model output based at least in part on the synthesized parameters.

17. The gas turbine engine of claim 16 , wherein the model is an engine parameter on-board synthesizer.

18. The gas turbine engine of claim 16 , wherein the element of a cycle of the gas turbine engine is an element of at least one of: a duct, a bleed, a pressure loss at a location, a turbine, a compressor, a diffusor, a burner, an exit guide vane, a nozzle, a fan, an efficiency loss module, a fan gear box, or a torque measurement.

19. The gas turbine engine of claim 16 , further comprising sensors to gather data associated with operation of the gas turbine engine, the data for use by the model.

20. The gas turbine engine of claim 16 , further comprising an analog-to-digital convertor to convert the data associated with operation of the gas turbine engine into a data format readable by the model.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Karpman Boris
• Niemczycki Thomas
• Dinsmore Ian Michael
• Sembiante David
• Luppold Robert H

Classifications

• G05B17/02 Primary

  electric · CPC title

• F02C7/26 Primary

  Starting; Ignition · CPC title

• F04D29/325

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

• G05B13/04

  involving the use of models or simulators · CPC title

• F05D2260/81

  Modelling or simulation · CPC title