Method for measuring the kinematics of at least one turbomachine rotor

#The present invention relates to a method for measuring the kinematics of at least one rotor of an engine, in particular of a turbine engine.

#The tests of a turbine engine are carried out either on a rig or in the open air and can be partial or not, i.e. they can involve the entire turbine engine or only a part thereof, such as one of the modules thereof.

#One of the objectives of the tests is to collect information about the actual behaviour of the turbine engine or of one of the modules thereof. Thus, the different physical parameters which are relevant for describing the operation of the turbine engine are to be acquired.

#The invention will be better understood, and other details, features and advantages of the invention will become apparent upon reading the following description, given by way of non-limiting example with reference to the accompanying drawings, in which:

#FIGS. 1A and 1B are schematic, perspective views of an installation for implementing the method according to the invention, from the front and from the side respectively,

#FIG. 2 is a very schematic front view of a rotor which is equipped with a ring for supporting radioactive tracers, and

#Reference is firstly made to FIGS. 1A and 1B, which show an installation 10 for implementing the method according to the invention for measuring the kinematics of a rotor of an engine, which in this case is an engine of a propulsion system 12.

#Conventionally, a propulsion system comprises an engine 14 of a turbine engine which is surrounded by a nacelle 16. The engine 14 comprises, from upstream to downstream, in the direction of flow, a fan 18, at least one compressor, a combustion chamber, at least one turbine and a pipe 20 for ejecting combustion gases. The propulsion system 12 is to be connected to a structural element of an aircraft, such as a wing or the fuselage thereof, by means of a strut 22 which is rigidly connected to the engine 14.

#In the case of a turbine engine or a bypass turbojet engine, the engine 14 defines a first annular flow duct for a primary flow or hot flow, and the nacelle 16 defines, around the engine 14, an annular flow duct for a secondary flow or cold flow. The air flow entering the air inlet of the nacelle 16 divides downstream of the fan 18 to form the above-mentioned primary and secondary air flows.