# US 11,078,849 B2 · Compact aero-thermo model based engine power control > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,078,849 B2 - Document ID: US11078849B2 - Status: Granted - Kind: B2 - Application number: 17/017,815 - Filed: 2020-09-11 - Published: 2021-01-07 - Granted: 2021-08-03 - Earliest claimed: 2013-03-15 - Assignees: Raytheon Technologies Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Boris Karpman; Richard P. Meisner; Matthew Donald; Thomas E. Case - Web page: https://patentgrep.com/patent/US11078849B2 ## 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 generating a model output using a model processor, processing a model input vector and setting a model operating mode, and setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode. Synthesized parameters are generated as a function of the dynamic states and the model input vector based on a series of utilities, where at least one of the utilities is a configurable utility including one or more sub-utilities. An estimated state of the model is determined based on at least one of a prior state and the synthesized parameters. An actuator associated with the control device is directed as a function of a model output, where the model output includes an estimated thrust value for the control device. ## Claims ### Claim 1 A control system, comprising: an actuator operable to adjust a control device; and a computer processor configured to execute a control law to control the actuator as a function of a model output of a model and generate the model output using a model processor, wherein the model processor comprises a plurality of executable instructions to: process a model input vector and set a model operating mode; set dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode; generate a plurality of synthesized parameters as a function of the dynamic states and the model input vector based on a series of utilities, wherein at least one of the utilities is a configurable utility comprising one or more sub-utilities; determine an estimated state of the model based on at least one of a prior state and the synthesized parameters; and process at least the synthesized parameters of the model to determine the model output comprising an estimated thrust value for the control device. ### Claim 2 (depends on 1) The control system of claim 1, wherein the control law compares the estimated thrust value with a goal value to determine a thrust control request, the thrust control request received by the actuator to control the thrust of the control device. ### Claim 3 (depends on 1) The control system of claim 1, wherein the control law applies control error to the estimated thrust signal to account for error in the control device. ### Claim 4 (depends on 3) The control system of claim 3, wherein the error in the control device is based on at least one of control law error, wear in the control device, customer power extraction, customer bleed extraction, humidity levels, and fuel quality. ### Claim 5 (depends on 1) The control system of claim 1, wherein the estimated thrust value of the control device is based on, at least, a spool speed of a spool of the control device. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 1) The control system of claim 1, wherein the control device is a gas turbine engine. ### Claim 8 (depends on 7) The control system of claim 7, wherein the utilities are based on physical laws that govern behavior of a component of the gas turbine engine. ### Claim 9 (depends on 7) The control system of claim 7, wherein the utilities model a plurality 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 of a model using a model processor; processing a model input vector and setting a model operating mode; setting dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode; generating a plurality of synthesized parameters as a function of the dynamic states and the model input vector based on a series of utilities, wherein at least one of the utilities is a configurable utility comprising one or more sub-utilities; determining an estimated state of the model based on at least one of a prior state and the synthesized parameters; 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, the model output comprising an estimated thrust value for the control device, using a control law; and adjusting the control device using the actuator. ### Claim 11 (depends on 10) The method of claim 10, wherein the control law compares the estimated thrust value with a goal value to determine a thrust control request, the thrust control request received by the actuator to control the thrust of the control device. ### Claim 12 (depends on 10) The method of claim 10, wherein the control law applies control error to the estimated thrust signal to account for error in the control device. ### Claim 13 (depends on 12) The method of claim 12, wherein the error in the control device is based on at least one of control law error, wear in the control device, customer power extraction, customer bleed extraction, humidity levels, or fuel quality. ### Claim 14 (depends on 10) The method of claim 10, wherein the estimated thrust value of the control device is based on, at least, a spool speed of a spool of the control device. ### Claim 15 (depends on 10) The method of claim 10, wherein the control device is a gas turbine engine, and the utilities model a plurality of physical processes associated with components of a thermodynamic cycle of the gas turbine engine. ### Claim 16 A gas turbine engine comprising: a fan; a compressor section downstream of the fan; a combustor section downstream of the compressor section; a turbine section downstream of the combustor section; an actuator operable to adjust 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 of a model using a model processor, wherein the model processor comprises a plurality of executable instructions to: process a model input vector and set a model operating mode; set dynamic states of the model processor, the dynamic states input to an open loop model based on the model operating mode; generate a plurality of synthesized parameters as a function of the dynamic states and the model input vector based on a series of utilities, wherein at least one of the utilities is a configurable utility comprising one or more sub-utilities; determine an estimated state of the model based on at least one of a prior state and the synthesized parameters; and process at least the synthesized parameters of the model to determine the model output. ### Claim 17 (depends on 16) The gas turbine engine of claim 16, wherein the control law compares an estimated thrust value with a goal value to determine a thrust control request, the thrust control request received by the actuator to control the thrust of the gas turbine engine. ### Claim 18 (depends on 16) The gas turbine engine of claim 16, wherein the control law applies control error to an estimated thrust signal to account for error in the gas turbine engine. ### Claim 19 (depends on 16) The gas turbine engine of claim 16, further comprising a spool, wherein an estimated thrust value of the gas turbine engine is based on, at least, a spool speed of the spool. ### Claim 20 (depends on 16) The gas turbine engine of claim 16, wherein the component comprises 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.