# US 2014/0150550 A1 · Method and system for integrating gas turbine trim balancing system into electronic engine controls > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0150550 A1 - Document ID: US20140150550A1 - Status: Published application - Kind: A1 - Application number: 13/689,855 - Filed: 2012-11-30 - Published: 2014-06-05 - Earliest claimed: 2012-11-30 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Pratt & Whitney Canada Corp. - Inventors: Paraag BORWANKAR; Heather GRANT; Enzo MACCHIA; Christopher MCELVAINE - Web page: https://patentgrep.com/patent/US20140150550A1 ## CPC - G01M 1/14: Determining imbalance (G01M1/30 takes precedence) - G01M 1/22: and converting vibrations due to imbalance into electric variables - G01M 15/12: by monitoring vibrations - G01M 15/14: Testing gas-turbine engines or jet-propulsion engines - G01M: TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR ## Abstract Methods and systems for determining a rebalancing strategy for trim balancing one or more rotational components of a gas turbine. One or more noise, acoustics or vibrational signals may be received at a control device of an aircraft comprising the gas turbine engine while the aircraft is in operation. The one or more noise, acoustics or vibrational signals may be used for determining a rebalancing strategy for one or more unbalanced rotational components. ## Claims ### Claim 1 A method for determining a rebalancing strategy for trim balancing one or more rotational components of a gas turbine, the method comprising: receiving one or more noise, acoustics or vibrational signals at a control device of an aircraft comprising the gas turbine engine while the aircraft is in operation; and using the one or more noise, acoustics or vibrational signals and one or more processors of the control device, determining a rebalancing strategy for one or more unbalanced rotational components. ### Claim 2 (depends on 1) The method of claim 1, wherein the control device is an electronic engine device. ### Claim 3 (depends on 1) The method of claim 1, the method further comprising determining whether at least one of the one or more rotational components is unbalanced and determining the rebalancing strategy only if at least one of the one or more rotational components is unbalanced. ### Claim 4 (depends on 3) The method of claim 3, wherein determining whether at least one of the one or more rotational components is unbalanced comprises determining whether at least one of the one or more noise, acoustics or vibrational signals exceeds a preset noise, acoustics or vibration threshold. ### Claim 5 (depends on 1) The method of claim 1, wherein the rebalancing strategy comprises a determination of how one or more weights attached to the one or more rotational components can be at least one of moved, added and removed, in order to rebalance the one or more rotational components. ### Claim 6 (depends on 1) The method of claim 1, wherein the rebalancing strategy comprises a determination of how one or more engine rotor airfoils can be at least one of relocated and repositioned, in order to rebalance the one or more rotational components. ### Claim 7 (depends on 1) The method of claim 1, wherein the rebalancing strategy comprises a determination of how one or more engine rotor airfoils can have material removed, in order to rebalance the one or more rotational components. ### Claim 8 (depends on 1) The method of claim 1, wherein the one or more noise, acoustics or vibrational signals are detected using one or more sensors coupled to the engine. ### Claim 9 (depends on 1) The method of claim 1, wherein data representing the one or more vibrational signals are stored in at least one memory of the control device. ### Claim 10 A control device of an aircraft comprising a gas turbine engine, the device useful for determining a rebalancing strategy for trim balancing one or more rotational components of the gas turbine engine, the device comprising: one or more receptors for receiving one or more noise, acoustics or vibrational signals from one or more sensors in the gas turbine engine while the aircraft is in operation; and one or more processors configured to determine a rebalancing strategy for one or more unbalanced rotational components. ### Claim 11 (depends on 10) The control device of claim 10, wherein the control device is an electronic engine device. ### Claim 12 (depends on 10) The control device of claim 10, wherein the one or more processors are further configured to determine whether at least one of the one or more rotational components is unbalanced and determine the rebalancing strategy only if at least one of the one or more rotational components is unbalanced. ### Claim 13 (depends on 12) The control device of claim 12, wherein the one or more processors are further configured to determine whether at least one of the one or more rotational components is unbalanced by determining whether at least one of the one or more noise, acoustics or vibrational signals exceeds a preset noise, acoustics or vibrational threshold. ### Claim 14 (depends on 10) The control device of claim 10, wherein the rebalancing strategy comprises a determination of how one or more weights attached to the one or more rotational components can be at least one of moved, added and removed in order to rebalance the one or more rotational components. ### Claim 15 (depends on 10) The control device of claim 10, wherein the rebalancing strategy comprises a determination of how one or more engine rotor airfoils can be at least one of relocated and repositioned, in order to rebalance the one or more rotational components. ### Claim 16 (depends on 10) The control device of claim 10, wherein the rebalancing strategy comprises a determination of how one or more engine rotor airfoils can have material removed, in order to rebalance the one or more rotational components. ### Claim 17 (depends on 10) The control device of claim 10, wherein the one or more noise, acoustics or vibrational signals are detected using one or more sensors attached to the engine. ### Claim 18 (depends on 10) The control device of claim 10, the control device further comprising at least one memory for storing data representing the one or more noise, acoustics or vibrational signals. ### Claim 19 (depends on 10) An aircraft comprising the device of claim 10.