Safran Aircraft Engines

Snecma

Safran

Julien Alexis Louis Ricordeau

Alexandre Anfriani

Cedrik Djelassi

Valerio Gerez

Jean-Michel Roux

Marc Missout

Cédrik Djelassi

Anthony Bernard Germain Lafitte

David Julien Boyer

Serge Christian Joel Blanchard

Augustin Marie Michel Descoqs

Quentin Sulli

A method for simulating the distribution of blades on a turbomachine disc includes: providing blade configurations, each being associated with a blade and including at least one measurement of a balancing parameter measured on the associated blade; and searching for and selecting a bladed-disc distribution combining the configurations of blades supplied with positions on the disc, the bladed disc distribution encouraging the attainment of at least one criterion defined according to a predetermined cost function dependent on the balancing parameter measurements, and the searching and selecting being performed by successive iterations.

Method for simulating the distribution of blades on a turbomachine disc

There is provided a method of and system for forecasting maintenance operations to be applied to an aircraft engine including a plurality of components monitored by damage counters, each damage counter being limited by a corresponding damage ceiling, the method including simulating consumption of the damage counters by iteratively drawing a series of simulation missions from a learning database; for each iteration, determining an accumulated consumption of each of the damage counters, until at least one damage counter related to a current simulation mission reaches a predetermined value limited by the damage ceiling associated with the damage counter; and applying a maintenance strategy on the current simulation mission to determine maintenance indicators representative of maintenance operations to be planned on the aircraft engine.

Forecasting maintenance operations to be applied to an engine

An aircraft turboprop engine has at least one low-pressure body and one high-pressure body. The low-pressure body drives a thrust propeller using a gearbox. The turboprop engine further includes a means for supplying air to an air-conditioning circuit of an aircraft cabin. The supply means includes a load compressor and a rotor that is coupled to the low-pressure body by the gearbox. The supply means further includes a means for controlling the rotation speed of the rotor of the compressor, which means comprise an electric motor, and a mechanical differential for coupling a first output shaft of said electric motor to a second output shaft of said gearbox and to said compressor rotor, such that the rotation speed of said rotor depends on the respective rotation speeds of said first and second output shafts.

Supply of air to an air-conditioning circuit of an aircraft cabin

A method of characterizing a turbine engine, the method comprising:

Avionics method and device for monitoring a turbomachine at startup

A system for controlling angular position of stator blades including: a mechanism for calculating a set angular position of the blades according to one of speeds; and a module for correcting the set position including: a mechanism for determining the angular position of the blades; a mechanism for measuring fuel flow rate of the turbine engine; a memory unit in which consecutive angular positions of the blades are combined with the fuel flow rates of the turbine engine measured at the angular positions; and a mechanism for determining a correcting angle according to the difference between the fuel flow rates measured between two consecutive angular position of the blades. A method for optimizing the common angular position can utilize the system.

System for controlling the angular position of stator blades and method for optimizing said angular position

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Paris, France

Julien Alexis Louis Ricordeau