# US 2018/0025557 A1 · Adaptive algorithm-based engine health prediction > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0025557 A1 - Document ID: US20180025557A1 - Status: Published application - Kind: A1 - Application number: 15/286,209 - Filed: 2016-10-05 - Published: 2018-01-25 - Earliest claimed: 2015-10-08 - Assignees: Bell Helicopter Textron Inc. - Applicants: Bell Helicopter Textron Inc. - Inventors: Alan H. STEINERT - Web page: https://patentgrep.com/patent/US20180025557A1 ## CPC - G07C 5/085: {using electronic data carriers} - B64D 45/00: Aircraft indicators or protectors not otherwise provided for - G05B 23/0221: {Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods} - G05B 23/0243: {model based detection method, e.g. first-principles knowledge model} - G06F 7/08: Sorting, i.e. grouping record carriers in numerical or other ordered sequence according to the classification of at least some of the information they carry (by merging two or more sets of carriers in ordered sequence G06F7/16) - G07C 5/008: {communicating information to a remotely located station (transmission systems for measured values G08C)} - G07C 5/0808: {Diagnosing performance data (testing of vehicles G01M17/00; testing of electrical installation on vehicles G01R31/005)} - G07C 5/0816: {Indicating performance data, e.g. occurrence of a malfunction} - B64D 2045/0085: {Devices for aircraft health monitoring, e.g. monitoring flutter or vibration} - G07C: TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - 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) - G06F: ELECTRIC DIGITAL DATA PROCESSING (computer systems based on specific computational models G06N) ## Abstract A system and algorithm-based method of determining engine health and assuring available propulsion power based on historical data reflecting the individual engine's unique performance “fingerprint.” ## Claims ### Claim 1 A method of collecting engine data for use in determining the health of an engine on an aircraft, the method comprising: receiving engine operating information; determining from the engine operating information a power parameter and a critical parameter; recording as a data point the power parameter and the critical parameter; and merging the data point with a stored data set, the stored data set including previously recorded power parameter and critical parameter data points. ### Claim 2 (depends on 1) The method according to claim 1, wherein receiving engine operating information includes receiving engine operating information from an aircraft data bus. ### Claim 3 (depends on 1) The method according to claim 1, wherein the critical parameter is an MGT value. ### Claim 4 (depends on 1) The method according to claim 1, wherein the power parameter is a power margin. ### Claim 5 (depends on 1) The method according to claim 1, further comprising receiving additional information relating to the aircraft or an operating environment. ### Claim 6 (depends on 5) The method according to claim 5, further comprising: correcting at least one of the power parameter and the critical parameter based on the additional information relating to the aircraft or the operating environment, wherein recording as a data point the power parameter and the critical parameter includes recording a corrected data point, the corrected data point including a corrected power parameter or a corrected critical parameter. ### Claim 7 (depends on 6) The method according to claim 6, wherein the corrected data point represents the engine's power if it were performing on a test stand under standard conditions. ### Claim 8 (depends on 1) The method according to claim 1, further comprising: determining whether the power parameter and the critical parameter represent a stable data point; and discarding the engine operating information in the event that the power parameter and the critical parameter do not represent a stable data point. ### Claim 9 (depends on 1) The method according to claim 1, further comprising: determining whether the power parameter and the critical parameter represent a valid data point; and discarding the engine operating information in the event that the power parameter and the critical parameter do not represent a valid data point. ### Claim 10 (depends on 1) The method according to claim 1, wherein merging the data point with a stored data set includes: grouping together the data point and a similar, previously recorded data point in the stored data set; and merging the grouped-together data points into a single, representative data point. ### Claim 11 (depends on 1) The method according to claim 1, further comprising purging a previously recorded data point from the stored data set. ### Claim 12 A method of determining the health of an engine on an aircraft, the method comprising: selecting an engine performance curve to use in creating an engine health model; executing a curve-fitting process to obtain a fitted curve, the fitted curve being based on the selected engine performance curve and a stored data set; evaluating engine health by comparing the fitted curve to a 100% specification-level performance curve for the engine; and outputting engine health information. ### Claim 13 (depends on 12) The method according to claim 12, wherein the selected engine performance curve includes the 100% specification-level performance curve for the engine. ### Claim 14 (depends on 12) The method according to claim 12, wherein executing a curve-fitting process to obtain a fitted curve includes translating the selected engine performance curve to achieve a low error with respect to the stored data set. ### Claim 15 (depends on 12) The method according to claim 12, wherein executing a curve-fitting process to obtain a fitted curve includes rotating the selected engine performance curve to achieve a low error with respect to the stored data set. ### Claim 16 (depends on 12) The method according to claim 12, wherein executing a curve-fitting process to obtain a fitted curve comprises: translating the selected engine performance curve to achieve a low error with respect to the stored data set; and rotating the selected engine performance curve to achieve a low error with respect to the stored data set, wherein the translating and rotating steps are achieved based on an optical fit. ### Claim 17 (depends on 12) The method according to claim 12, wherein evaluating engine health by comparing the fitted curve to a 100% specification-level performance curve for the engine includes evaluating margins between the fitted curve and the 100% specification-level performance curve at various points to determine an overall estimate of engine health. ### Claim 18 (depends on 12) The method according to claim 12, wherein evaluating engine health by comparing the fitted curve to a 100% specification-level performance curve for the engine includes evaluating a margin between the fitted curve and the 100% specification-level performance curve at a chosen point to determine an expected power margin at the chosen point. ### Claim 19 (depends on 12) The method according to claim 12, wherein outputting engine health information includes one of: providing engine health information to a flight crew interface device; storing engine health information in a data storage device; and transmitting engine health information via a transceiver device. ### Claim 20 A method of determining the health of an engine on an aircraft, the method comprising: receiving engine operating information; determining from the engine operating information a power parameter and a critical parameter; recording as a data point the power parameter and the critical parameter; merging the data point with a stored data set, the stored data set including previously recorded power parameter and critical parameter data points; selecting an engine performance curve to use in creating an engine health model; obtaining a fitted curve by translating and rotating the selected engine performance curve to achieve a low error with respect to the stored data set; evaluating engine health by comparing the fitted curve to a 100% specification-level performance curve for the engine; and outputting engine health information.