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An adaptive aero-thermodynamic engine model is disclosed which incorporates a plurality of model engine operating parameters, a plurality of nominal component efficiencies and corresponding efficiency modifier functions. The engine model is adapted by measuring a plurality of engine operating parame

An adaptive aero-thermodynamic engine model is disclosed which incorporates a plurality of model engine operating parameters, a plurality of nominal component efficiencies and corresponding efficiency modifier functions. The engine model is adapted by measuring a plurality of engine operating parameters corresponding to the plurality of model engine operating parameters during steady state operation of the engine over a plurality of data points, matching each of the model engine operating parameters to respective measured engine operating parameters by iteratively adapting each of the nominal component efficiencies using the corresponding efficiency modifier functions, estimating actual component efficiencies based upon the adapted nominal component efficiencies, and inputting the estimated actual component efficiencies into the engine model.

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What is claimed is: 1. A processor-based method of adapting an aero-thermodynamic engine model for a turboshaft engine comprising the steps of: a) providing an adaptive aero-thermodynamic engine model incorporating a plurality of model engine operating parameters, a plurality of nominal component e

What is claimed is: 1. A processor-based method of adapting an aero-thermodynamic engine model for a turboshaft engine comprising the steps of: a) providing an adaptive aero-thermodynamic engine model incorporating a plurality of model engine operating parameters, a plurality of nominal component efficiencies and corresponding efficiency modifier functions; b) measuring a plurality of engine operating parameters corresponding to the plurality of model engine operating parameters during steady state operation of the engine over a plurality of data points; c) matching each of the model engine operating parameters to respective measured engine operating parameters by iteratively adapting each of the nominal component efficiencies using the corresponding efficiency modifier functions; d) estimating actual component efficiencies based upon the adapted nominal component efficiencies; and e) inputting the estimated actual component efficiencies into the engine model. 2. A processor-based method of adapting an aero-thermodynamic engine model according to claim 1, further comprising the step of predicting maximum engine power availability based on the adapted engine model. 3. A method of adapting an aero-thermodynamic engine model according to claim 1, further comprising the step of detecting engine sensor failures based on the adapted engine model. 4. A processor-based method of adapting an aero-thermodynamic engine model according to claim 1, further comprising the step of controlling the engine based on the adapted engine model. 5. A processor-based method of adapting an aero-thermodynamic engine model according to claim 1, wherein the step of matching the model engine operating parameters to respective measured engine operating parameters includes the step of minimizing a combined measurement error between the model engine operating parameters and the measured engine operating parameters. 6. A processor-based method of adapting an aero-thermodynamic engine model according to claim 5, wherein the step of minimizing the combined measurement error is terminated when a predetermined condition is met. 7. A processor-based method of adapting an aero-thermodynamic engine model according to claim 1, further comprising the step of calibrating an input fuel flow to the engine by measuring the input fuel flow during steady state operation over a plurality of data points, iteratively adapting the input fuel flow using a fuel flow modifier function, and estimating the actual value of the input fuel flow based upon the adapted input fuel flow, wherein the estimated actual value of the input fuel flow is an input to the engine model. 8. A processor-based method of adapting an aero-thermodynamic engine model according to claim 1, further comprising the step of calibrating an inlet guide vane angle of the engine by measuring the inlet guide vane angle during steady state operation over a plurality of data points, iteratively adapting the inlet guide vane angle using an inlet guide vane angle modifier function, and estimating the actual value of the inlet guide vane angle based upon the adapted inlet guide vane angle, wherein the estimated actual value of the inlet guide vane angle is an input to engine model. 9. An electronic control unit having an embedded adaptive aero-thermodynamic engine model for a turboshaft engine comprising: a) means for storing a plurality of model engine operating parameters and a plurality of nominal engine component efficiencies and corresponding efficiency modifier functions; b) means for receiving a plurality of measured engine operating parameters; and c) means for estimating actual engine component efficiencies by matching the model engine operating parameters to the measured engine operating parameters. 10. An electronic control unit having an embedded adaptive aero-thermodynamic engine model as recited in claim 9, wherein the means for estimating actual engine component efficiencies includes means for iteratively adapting each of the nominal component efficiencies using the corresponding efficiency modifier functions. 11. An electronic control unit having an embedded adaptive aero-thermodynamic engine model as recited in claim 9, further comprising means for estimating an actual input fuel flow to the engine. 12. An electronic control unit having an embedded adaptive aero-thermodynamic engine model as recited in claim 11, wherein the means for estimating an actual input fuel flow to the engine includes a fuel flow modifier function for iteratively adapting a measured input fuel flow. 13. An electronic control unit having an embedded adaptive aero-thermodynamic engine model as recited in claim 9, further comprising means for estimating an actual inlet guide vane angle for the engine. 14. An electronic control unit having an embedded adaptive aero-thermodynamic engine model as recited in claim 13, wherein the means for estimating an actual inlet guide vane angle for the engine includes an inlet guide vane modifier function for iteratively adapting a measured inlet guide vane angle.