Patent ID: 9482237
Filing Date: 2016-11-01
CPC Classification: F04D

Claim Text:
1. A method for modifying a multi stage compressor of a turbomachine, the method comprising: providing the multi stage compressor, each compressor stage comprising a rotor blading and a stator blading each formed of an annular array of blades; determining a number of blades of at least one of each rotor blading and each stator blading for each stage of the compressor; creating a computer model of at least one of each rotor blading and each stator blading of the compressor; determining by instationary computations trajectories of slipstreams of trailing edges of the blades of at least one of a rotor blading and a stator blading of an upstream stage n to leading edges of blades of at least one of a rotor blading and a stator blading of a downstream stage n+1 in the computer model; positioning angularly the at least one of the rotor blading and the stator blading of the downstream stage n+1 in the computer model so that the slipstreams pass between the leading edges of the blades of the at least one of the rotor blading and the stator blading of the downstream stage n+1, substantially in a middle of inter blade circumferential spaces; repeating the determining by instationary computations and the positioning for all the stages of the computer model, from upstream to downstream, in order to achieve an aerodynamic coupling on all of at least one of the rotor bladings and stator bladings of the compressor; validating the respective positions of at least one of the rotor bladings and the stator bladings by new instationary computations on the entire compressor; and modifying the positions of at least one of the rotor bladings and the stator bladings based on the positioning.