Diagnosis of aircraft gas turbine engines
First Claim
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1. A method for the at least partially automated diagnosis of aircraft gas turbine engines, comprising:
- detecting actual parameter values of an aircraft gas turbine engine for several operational segments with sensors disposed within the aircraft gas turbine engine, the sensor types include at least one of a temperature sensor, a pressure sensor, a mass flow sensor, and a rotational speed sensor, the parameter values comprising temperatures in one or more operational segments of the gas turbine, pressures in one or more stages of the gas turbine, fuel consumption and/or fuel mass flow, and rotational speed values of a rotor of the aircraft gas turbine engine;
determining deviation, of these actual parameter values from theoretical parameter values of the operation of the aircraft gas turbine engine;
determining damage pattern probabilities based on a similarity of at least one determined deviation to deviation patterns of various known damage patterns to aircraft gas turbine engines;
determining a damage pattern probability for an unknown damage pattern; and
generating an error message if at least one determined deviation exceeds a predetermined limit value,wherein damage patterns and/or causes comprise components, subassemblies, and/or defects.
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Abstract
A method for the at least partially automated diagnosis of aircraft gas turbine engines includes the steps of: 1) detecting actual parameter values of an aircraft gas turbine engine for several operational segments 2) determining deviations, of these actual parameter values from theoretical parameter values; and 3) determining damage pattern probabilities based on a similarity of at least one determined deviation, particularly based on a change between determined deviations, to deviation patterns of different known damage patterns.
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13 Claims
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1. A method for the at least partially automated diagnosis of aircraft gas turbine engines, comprising:
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detecting actual parameter values of an aircraft gas turbine engine for several operational segments with sensors disposed within the aircraft gas turbine engine, the sensor types include at least one of a temperature sensor, a pressure sensor, a mass flow sensor, and a rotational speed sensor, the parameter values comprising temperatures in one or more operational segments of the gas turbine, pressures in one or more stages of the gas turbine, fuel consumption and/or fuel mass flow, and rotational speed values of a rotor of the aircraft gas turbine engine; determining deviation, of these actual parameter values from theoretical parameter values of the operation of the aircraft gas turbine engine; determining damage pattern probabilities based on a similarity of at least one determined deviation to deviation patterns of various known damage patterns to aircraft gas turbine engines; determining a damage pattern probability for an unknown damage pattern; and generating an error message if at least one determined deviation exceeds a predetermined limit value, wherein damage patterns and/or causes comprise components, subassemblies, and/or defects. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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