METHOD TO ESTIMATE AIRCRAFT GAS TURBINE ENGINE STATE Russian patent published in 2010 - IPC G01M15/14 

FIELD: aircraft engineering.

SUBSTANCE: proposed method is intended for estimating aircraft gas turbine engine state. Additionally, proposed method comprises determining and/or measuring thermo- and gas-dynamic parametres X of the engine that define thermodynamic load of major parts of the engine. Also, parametres y_i of said thermodynamic loads are calculated. Note here that aforesaid tolerances are preset from the results of cyclic tests carried out outside said engine. Note also the 1^st functional dependence between parameters X_o, X and parametres y_i is preliminary set, as well as 2^nd functional dependence between parametres y_i and those of stress σ_i and strain ∈_i of all major parts, to allow calculating σ_i and ∈_i of every major part in the conditions of particular flight. Actual wear of each major part is calculated from criteria of long-term strength P_iΣ"ч" and cyclic damageability P_iΣ"ец". In case magnitudes of said criteria exceed tolerable maximum magnitudes of [P_iΣ"ч"] and [P_iΣ"ц"], engine operation is terminated.

EFFECT: increasing efficiency of aircraft gas turbine engine by reducing costs of determining tolerances used as criteria of engine wear and at increasing accuracy of estimating actual state of said engine by continuous control over its all assembly units and parts in particular operating conditions.

2 cl, 2 dwg