# US 2024/0200465 A1 · Methods and apparatus to target engine operating cycle conditions for clearance control > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2024/0200465 A1 - Document ID: US20240200465A1 - Status: Published application - Kind: A1 - Application number: 18/085,261 - Filed: 2022-12-20 - Published: 2024-06-20 - Earliest claimed: 2022-12-20 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Timothy M. Kasberg; Timothy L. Schelfaut; Brendon Leeker; Kevin Graziano; Massimo Rufo; Tyler F. Hooper - Web page: https://patentgrep.com/patent/US20240200465A1 ## CPC - F01D 15/10: Adaptations for driving, or combinations with, electric generators - F01D 11/24: by selectively cooling-heating stator or rotor components - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract Methods, apparatus, systems, and articles of manufacture are disclosed. An example hybrid-electric gas turbine engine comprises: a first motor coupled to a first rotatable component; a second motor coupled to a second rotatable component; and control circuitry to: determine a current operating clearance of the hybrid-electric gas turbine engine; identify one or more parameters of a model of the hybrid-electric gas turbine engine for modification based on a difference between the current operating clearance and a desired operating clearance of the hybrid-electric gas turbine engine; and modulate power to at least one of the first motor or the second motor based on the identified one or more parameters to satisfy the desired operating clearance and maintain a thrust of the hybrid-electric gas turbine engine. ## Claims ### Claim 1 A hybrid-electric gas turbine engine comprising: a first motor coupled to a first rotatable component; a second motor coupled to a second rotatable component; and control circuitry to: determine a current operating clearance of the hybrid-electric gas turbine engine; identify one or more parameters of a model of the hybrid-electric gas turbine engine for modification based on a difference between the current operating clearance and a desired operating clearance of the hybrid-electric gas turbine engine; and modulate power to at least one of the first motor or the second motor based on the identified one or more parameters to satisfy the desired operating clearance and maintain a thrust of the hybrid-electric gas turbine engine. ### Claim 2 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the control circuitry is to adjust one or more components of the hybrid-electric gas turbine engine to alter a blade tip deflection based on the identified one or more parameters. ### Claim 3 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the first rotatable component is a low pressure spool. ### Claim 4 (depends on 3) The hybrid-electric gas turbine engine of claim 3, wherein the second rotatable component is a high pressure spool. ### Claim 5 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the one or more parameters of the model includes at least one of a speed of gas in the hybrid-electric gas turbine engine, a flow of gas in the hybrid-electric gas turbine engine, a pressure of gas in the hybrid-electric gas turbine engine, or a temperature of gas in the hybrid-electric gas turbine engine. ### Claim 6 (depends on 5) The hybrid-electric gas turbine engine of claim 5, further including a third motor coupled to a third spool, wherein the control circuitry is to modulate power to the third motor to meet the desired operating clearance. ### Claim 7 (depends on 6) The hybrid-electric gas turbine engine of claim 6, further including one or more additional motors coupled to one or more respective spools. ### Claim 8 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the identified one or more parameters are adjusted based on a bore circuit pressure of the hybrid-electric gas turbine engine. ### Claim 9 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the desired operating clearance is an axial clearance between a rotor and a stator of a compressor or turbine of the hybrid-electric gas turbine engine, and the identified one or more parameters are adjusted based on a total deflection between the rotor and the stator. ### Claim 10 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the desired operating clearance is a seal clearance or a buffer cavity clearance of the hybrid-electric gas turbine engine. ### Claim 11 (depends on 1) The hybrid-electric gas turbine engine of claim 1, wherein the model of the gas turbine engine is generated based on data obtained from sensors placed throughout the gas turbine engine. ### Claim 12 A system comprising: at least one memory; programmable circuitry; and instructions to cause the programmable circuitry to: determine a current operating clearance of a gas turbine engine including a first motor coupled to a first rotatable component and a second motor coupled to a second rotatable component; identify one or more parameters of a model of the gas turbine engine for modification based on a difference between the current operating clearance and a desired operating clearance of the gas turbine engine; and modulate power to at least one of the first motor or the second motor based on the identified one or more parameters to satisfy the desired operating clearance and maintain a thrust of the gas turbine engine. ### Claim 13 (depends on 12) The system of claim 12, wherein the programmable circuitry is to adjust one or more components of the gas turbine engine to alter a blade tip deflection based on the identified one or more parameters. ### Claim 14 (depends on 12) The system of claim 12, wherein the first rotatable component is a low pressure spool. ### Claim 15 (depends on 14) The system of claim 14, wherein the second rotatable component is a high pressure spool. ### Claim 16 (depends on 12) The system of claim 12, wherein the gas turbine engine is a hybrid-electric engine and the one or more parameters of the model includes at least one of a speed of gas in the gas turbine engine, a flow of gas in the gas turbine engine, a pressure of gas in the gas turbine engine, or a temperature of gas in the gas turbine engine. ### Claim 17 (depends on 12) The system of claim 12, further including one or more additional motors coupled to one or more respective spools. ### Claim 18 A method comprising: determining a current operating clearance of a gas turbine engine, the gas turbine engine including a first motor coupled to a first rotatable component and a second motor coupled to a second rotatable component; identifying one or more parameters of a model of the gas turbine engine for modification based on a difference between the current operating clearance and a desired operating clearance of the gas turbine engine; and modulating power to at least one of the first motor or the second motor based on the identified one or more parameters to satisfy the desired operating clearance and maintain a thrust of the gas turbine engine. ### Claim 19 (depends on 18) The method of claim 18, further including adjusting one or more components of the gas turbine engine and altering a blade tip deflection based on the identified parameters. ### Claim 20 (depends on 18) The method of claim 18, wherein the first rotatable component is a low pressure spool, and wherein the second rotatable component is a high pressure spool.