# US 10,767,563 B2 · Compact aero-thermo model based control system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,563 B2 - Document ID: US10767563B2 - Status: Granted - Kind: B2 - Application number: 16/203,995 - Filed: 2018-11-29 - Published: 2019-03-28 - Granted: 2020-09-08 - Earliest claimed: 2013-03-15 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Boris Karpman; Thomas Niemczycki; Ian Michael Dinsmore; David Sembiante; Robert H. Luppold - Web page: https://patentgrep.com/patent/US10767563B2 ## CPC - F02C 7/26: Starting; Ignition - F01D 21/003: {Arrangements for testing or measuring (for measuring vibrations G01H)} - F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) - F02C 9/16: Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) - F02C 9/20: by throttling; by adjusting vanes - F04D 29/321: {for axial flow compressors} - F04D 29/325: {for axial flow fans (blade mountings F04D29/34, blades F04D29/38)} - G05B 13/04: involving the use of models or simulators - G05B 17/02: electric - G05B 23/0254: {based on a quantitative model, e.g. mathematical relationships between inputs and outputs; functions: observer, Kalman filter, residual calculation, Neural Networks} - G05D 7/0629: {characterised by the type of regulator means} - F05D 2220/32: in gas turbines - F05D 2240/35: Combustors or associated equipment - F05D 2260/81: Modelling or simulation - F05D 2260/85: Starting - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - G05B: CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS (systems for controlling or regulating non-electric variables G05D; systems for regulating electric or magnetic variables G05F; control devices or systems insofar as characterised by mechanical features only G05G) - G05D: SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) The control system of claim 1, further comprising system sensors to contribute data to the model input vector. ### Claim 4 (depends on 1) The control system of claim 1, wherein the cycle synthesis modules comprise at least one configurable utility comprising one or more sub-utilities. ### Claim 5 (depends on 4) The control system of claim 4, wherein at least one configurable utility is designed to model physical processes of a compressor element. ### Claim 6 (depends on 4) The control system of claim 4, wherein at least one configurable utility is designed to model physical processes of a turbine element. ### Claim 7 (depends on 1) 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. ### Claim 8 (depends on 1) The control system of claim 1, wherein the control device is a gas turbine engine. ### Claim 9 (depends on 8) 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. ### Claim 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. ### Claim 11 (depends on 10) The method of claim 10, further comprising receiving instructions by the model via an operator interface operatively associated with the control device. ### Claim 12 (depends on 10) The method of claim 10, wherein the control device is a gas turbine engine. ### Claim 13 (depends on 12) The method of claim 12, wherein the model is an engine parameter on-board synthesizer. ### Claim 14 (depends on 12) 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. ### Claim 15 (depends on 10) The method of claim 10, wherein the cycle synthesis modules comprise at least one of configurable utility comprising one or more sub-utilities. ### Claim 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. ### Claim 17 (depends on 16) The gas turbine engine of claim 16, wherein the model is an engine parameter on-board synthesizer. ### Claim 18 (depends on 16) 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. ### Claim 19 (depends on 16) 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. ### Claim 20 (depends on 16) 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.