Abstract: A method for engine performance degradation prediction based on the EC-RBELM algorithm, including establishing a prediction model cluster for three performance parameters, i.e., gas turbine speed Ng, power turbine inlet temperature T45 and specific fuel consumption SFC, in different atmospheric environments based on the EC-RBELM algorithm; learning EC-RBELM network topology parameters offline and automatically updating EC-RBELM network topology parameters based on prediction errors; and predicting the degradation of individual performance parameters of the turboshaft engine in different atmospheric environments according to the EC-RBELM algorithm model.

Abstract: An aircraft engine includes an outer casing, an inner casing, a first rotating shaft, a first fan, a second fan, a first combustor, and a second combustor. The outer casing has an outer intake end and an outer exhaust end. The inner casing includes a first section and a second section arranged in an axial direction. The first rotating shaft is rotatably disposed in the inner casing. The first fan includes an inner turbine portion, a first connection portion, and an outer turbine portion. The second fan is connected to the first rotating shaft and disposed on the outer intake end side of the first section wherein an outer diameter of the second fan is larger than that of the first section. The first combustor is disposed between the second fan and the outer turbine portion. The second combustor is disposed between the second fan and the inner turbine portion.