Patent ID: 8918264
Filing Date: 2014-12-23
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. An aiding method for monitoring at least one turbine engine of an aircraft, the method comprising the following operations, carried out automatically and repeatedly: (a) measuring, by a parameter measurement device, at least one temperature relating to the turbine engine; (b) determining, by an information processing unit/calculator, a value illustrating a thermomechanical condition of the turbine engine, the value illustrating the thermomechanical condition being determined by a calculation method and being dependent on thermal conditions identified by the at least one temperature that has been measured, wherein the value illustrating the thermomechanical condition identifies differential expansion between elements of the turbine engine that can lead to undesired frictional contact and damage of the elements and that can also lead to rotor lock; (c) comparing, by the information processing unit/calculator, the determined value illustrating the thermomechanical condition with at least one predetermined threshold value; and (d) showing, by a display device, at least one indication on a cockpit viewing screen of the aircraft, depending on the comparison of step (c), the at least one indication relating to operation of the turbine engine and including at least one of the following indications: