Engine monitoring
First Claim
1. A method comprising:
- monitoring, by a processor, a gas turbine engine across a flight envelope of an aircraft powered by the gas turbine engine, the monitoring comprising;
measuring, by a processor, one or more operating parameters of the gas turbine engine and a performance parameter of the gas turbine engine during one or more operational periods of the gas turbine engine;
recording, by a processor, a plurality of data points, each data point comprising the operating parameters and the associated performance parameter;
identifying, by a processor, one or more steady state regions in the performance parameter and selecting a plurality of the data points from the one or more steady state regions in the performance parameter;
selecting, by a processor, one or more groups of the steady state data points in the operating parameter space by virtue of a predetermined density of the steady state data points in the operating parameter space;
comparing, by a processor, the performance parameter within the groups so as to identify a change in the performance of the gas turbine engine;
counting, by a processor, the number of steady state data points neighbouring a particular steady state data point within a predetermined domain about the particular steady state data point in the operating parameter space;
repeating, by a processor, for each steady state data point; and
grouping, by a processor, steady state data points with a number of neighbouring steady state data points above a predetermined threshold into the one or chore groups, wherein all points defining a boundary of the predetermined domain in the operating parameter space are equidistant from the particular steady state data point.
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Accused Products
Abstract
A method of monitoring a device, the method comprising: measuring one or more device operating parameters and a device performance parameter during one or more device operational periods; recording a plurality of data points, each data point comprising the device operating parameters and the associated device performance parameter; identifying one or more steady state regions in the device performance parameter and selecting a plurality of the data points from the one or more steady state regions in the device performance parameter; selecting one or more groups (40) of the steady state data points in the device operating parameter space by virtue of a predetermined density of the steady state data points in the device operating parameter space; and comparing the device performance parameter within the groups so as to identify a change in the performance of the device.
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Citations
16 Claims
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1. A method comprising:
monitoring, by a processor, a gas turbine engine across a flight envelope of an aircraft powered by the gas turbine engine, the monitoring comprising; measuring, by a processor, one or more operating parameters of the gas turbine engine and a performance parameter of the gas turbine engine during one or more operational periods of the gas turbine engine; recording, by a processor, a plurality of data points, each data point comprising the operating parameters and the associated performance parameter; identifying, by a processor, one or more steady state regions in the performance parameter and selecting a plurality of the data points from the one or more steady state regions in the performance parameter; selecting, by a processor, one or more groups of the steady state data points in the operating parameter space by virtue of a predetermined density of the steady state data points in the operating parameter space; comparing, by a processor, the performance parameter within the groups so as to identify a change in the performance of the gas turbine engine; counting, by a processor, the number of steady state data points neighbouring a particular steady state data point within a predetermined domain about the particular steady state data point in the operating parameter space; repeating, by a processor, for each steady state data point; and grouping, by a processor, steady state data points with a number of neighbouring steady state data points above a predetermined threshold into the one or chore groups, wherein all points defining a boundary of the predetermined domain in the operating parameter space are equidistant from the particular steady state data point. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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14. A non-transitory computer-readable medium containing instructions, which when executed on a computer, carries out the following:
monitoring, by a processor, a gas turbine engine across a flight envelope of an aircraft powered by the gas turbine engine, the monitoring comprising; measuring, by the processor, one or more operating parameters of the gas turbine engine and a performance parameter of the gas turbine engine during one or more operational periods of the gas turbine engine; recording, by the processor, a plurality of data points, each data point comprising the operating parameters and the associated performance parameter; identifying, by the processor, one or more steady state regions in the performance parameter and selecting a plurality of the data points from the one or more steady state regions in the performance parameter; selecting, by the processor, one or more groups of the steady state data points in the operating parameter space by virtue of a predetermined density of the steady state data points in the operating parameter space; comparing, by the processor, the performance parameter within the groups so as to identify a change in the performance of the gas turbine engine; counting, by the processor, the number of steady state data points neighbouring a particular steady state data point within a predetermined domain about the particular steady state data point in the operating parameter space; repeating, by the processor, for each steady stat data point; and grouping, by the processor, steady state data points with a number of neighbouring steady state data points above a predetermined threshold into the one or more groups, wherein all points defining a boundary of the predetermined domain in the operating parameter space are equidistant from the particularly steady state data point.
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15. An apparatus for monitoring a gas turbine engine, the apparatus comprising a computer storage medium configured to store a computer program and a processor configured to execute the program to:
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monitor a gas turbine engine across a flight envelope of an aircraft powered by the gas turbine engine, receive one or more operating parameters of the gas turbine engine and a performance parameter of the gas turbine engine during one or more operational periods of the gas turbine engine; record a plurality of data points, each data point comprising the operating parameters and the associated performance parameter; identify one or more steady state regions in the performance parameter and select a plurality of the data points from the one or more steady state regions in the performance parameter; select one or more groups of the steady state data points in the operating parameter space by virtue of a predetermined density of the steady state data points in the operating parameter space; compare the performance parameter within the groups so as to identify a change in the performance of the gas turbine engine; count the number of steady state data points neighbouring a particular steady state data point within a predetermined domain about the particular steady state data point in the operating parameter space; repeat for each steady state data point; and group steady state data points with a number of neighbouring steady state data points above a predetermined threshold into the one or more groups, wherein all points defining a boundary of the predetermined domain in the operating parameter space are equidistant from the particular steady state data point.
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16. A method comprising:
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monitoring, by a processor, a gas turbine engine across a flight envelope of an aircraft powered by the gas turbine engine, the monitoring comprising; measuring, by a processor, one or more operating parameters of the gas turbine engine and a performance parameter of the gas turbine engine during one or more operational periods of the gas turbine engine; recording, by a processor, a plurality of data points, each data point comprising the operating parameters and the associated performance parameter; identifying, by a processor, one or more steady state regions in the performance parameter and selecting a plurality of the data points from the one or more steady state regions in the performance parameter; selecting, by a processor, one or more groups of the steady state data points in the operating parameter space by virtue of a predetermined density of the steady state data points in the operating parameter space; comparing, by a processor, the performance parameter within the groups so as to identify a change in the performance of the gas turbine engine; counting, by a processor, the number of steady state data points neighboring a particular steady state data point within a predetermined domain about the particular steady state data point in the operating parameter space; repeating, by a processor, for each steady state data point; grouping, by a processor, steady state data points with a number of neighboring steady state data points above a predetermined threshold into the one or more groups; calculating the distances between a steady state data point within the one or more groups and each of the remaining steady state data points within the one or more groups in the operating parameter space; and identifying the steady state data points within a group by virtue of their proximity to one another so as to distinguish between the one or more groups.
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Specification