Abstract: Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel onto which the duct discharges, and a pre-rotation grille which is positioned in the air inlet duct upstream of the movable compressor wheel in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes, the assembly being characterized in that the pitch between two consecutive vanes of the grille is greater than the chord of one of the two vanes at a given height of the air duct, preferably in its upper part.

Abstract: Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel onto which the duct discharges, and a pre-rotation grille which is positioned in the air inlet duct upstream of the movable compressor wheel in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes, the assembly being characterized in that the pitch between two consecutive vanes of the grille is greater than the chord of one of the two vanes at a given height of the air duct, preferably in its upper part.

Abstract: A method of checking turbomachine blades is presented that may be implemented using a computer and a measuring device. Turbomachine blades compatible with embodiments of the method have a profile including a centerline, suction face, pressure face, leading edge and trailing edge. The method measures geometrical coordinates of many points on a blade section profile, calculates an aerodynamic parameter of the blade section as a function of the measured coordinates, verifies whether the calculated aerodynamic parameter value departs from a valid range of parameters from a reference blade, and validates or rejects the blade depending upon whether the value of the aerodynamic parameter falls within the valid range.

Abstract: The present invention relates to the checking of turbomachine blades having a profile comprising a centerline, a suction face, a pressure face, a leading edge and a trailing edge, consisting in: measuring geometrical coordinates of a plurality of points located on the profile of at least one blade section; calculating at least one aerodynamic parameter of the blade section as a function of the measured coordinates; verifying whether the value of the calculated aerodynamic parameter departs from a validity range defined by a value of the nominal aerodynamic parameter of a reference blade and an associated tolerance; and validating the blade if the value of the aerodynamic parameter falls within the validity range or rejecting the blade if the value of the aerodynamic parameter lies outside the validity range. The present invention also relates to a computer program, which can be loaded directly into the memory of a computer, intended to implement the method according to the invention.

Abstract: A method for the early detection of aerodynamic instability in a turbomachine compressor is described which involves collecting and normalizing signals from sensors distributed uniformly around the circumference of the compressor and detecting events for which the normalized signals do not pass through a zero value during a length of time Tz which is at least greater than the time taken for two successive moving blades to travel past the sensor. A decision regarding the imminence of aerodynamic instability is then taken after the detected events have been analyzed and decision criteria have been applied. The decision criteria may be based on the event detection rate and/or on the spatio-temporal position of the events detected across all the sensors.

Abstract: A method for the early detection of aerodynamic instability in a turbomachine compressor is described which involves collecting and normalizing signals from sensors distributed uniformly around the circumference of the compressor and detecting events for which the normalized signals do not pass through a zero value during a length of time Tz which is at least greater than the time taken for two successive moving blades to travel past the sensor. A decision regarding the imminence of aerodynamic instability is then taken after the detected events have been analyzed and decision criteria have been applied. The decision criteria may be based on the event detection rate and/or on the spatio-temporal position of the events detected across all the sensors.