System and method for continuous performance analysis of systems that exhibit variable performance characteristics at different operating conditions

A method of translating performance characteristics for a gas turbine engine from one engine condition to another engine condition, comprising the steps of:

• sensing, at a current engine condition, a first engine performance parameter and a second engine performance parameter, the first and second engine performance parameters corresponding to a measured performance characteristic value of the engine;
• retrieving, from a memory, a first reference performance datum associated with the first and second engine performance parameters at the current engine condition;
• retrieving, from the memory, a second reference performance datum associated with the first and second engine performance parameters at a selected reference engine condition;
• calculating, in a processor, a difference between the first reference performance datum and the second reference performance datum, to thereby generate a translation value;
• and
• translating, in the processor, the measured performance characteristic value of the engine an amount equal to the data translation value, to thereby generate a corrected performance characteristic value of the engine at the selected reference engine condition.

A gas turbine engine continuous performance analysis system, comprising:

• a first sensor operable to sense, at a current flight condition, a first engine performance parameter and supply first engine performance parameter data representative of the first engine performance parameter;
• a second sensor operable to sense, at the current flight condition, a second engine performance parameter and supply second engine performance parameter data representative of the second engine performance parameter;
• memory having stored therein reference performance data associated with the first and second engine performance parameters at a plurality of flight conditions;
• and
• a processor in operable communication with the first sensor, the second sensor, and the memory, the processor coupled to receive the first and second engine performance parameter data from the first and second sensors, respectively, and configured, upon receipt thereof, to:
• retrieve, from the memory, a first reference performance datum associated with the first and second engine performance parameters at the current flight condition;
• retrieve, from the memory, a second reference performance datum associated with the first and second engine performance parameters at a selected reference flight condition;
• calculate a difference between the first reference performance datum and the second reference performance datum, to thereby generate a translation value;
• and
• translate the measured performance characteristic value of the engine an amount equal to the data translation value, to thereby generate a corrected performance characteristic value of the engine at the selected reference flight condition.