Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor

#The present document claims priority to French patent application Ser. No. 04 52 202 filed Sep. 30, 2004, which is hereby incorporated herein by reference.

#This invention relates to the field of turbomachine compressors, and particularly to aircraft engine compressors.

#It relates to an air circulation method in a turbomachine compressor.

#The invention will be better understood after reading the detailed description of embodiments of the invention given below for illustrative purposes only and that is in no way limitative, with reference to the attached drawings in which:

#FIG. 1, diagrammatically illustrates a partial section showing a conventional arrangement of a turbomachine compressor;

#FIG. 2 diagrammatically illustrates a partial section showing a first embodiment of the air circulation method and the compressor arrangement according to the invention;

#FIG. 1 diagrammatically and partially illustrates a conventional compressor, in a longitudinal section passing between the vanes and the blades. It comprises a central hub (not shown) with axis 2, an inner approximately annular casing 4 around the hub, delimiting an inner chamber 6 of the compressor and an approximately annular outer chamber 8 around the inner casing 4. The inner casing 4 and the outer casing 8 delimit a flowpath 10 between them along which a main airflow denoted by the arrow 12 in FIG. 1 passes. The arrow 12 defines a flow direction from the upstream side (to the left in the figure) towards the downstream side (to the right in the figure).

#The compressor comprises rotors 14, each comprising a disk 16 with axis 2 prolonged by blades 18 distributed around its periphery. The rotors 14 are arranged in the compressor, such that the blades 18 are located in the flowpath 10. The rotors 14 are also connected together through the inner casing 4, approximately at their base 19 through which they are anchored to the corresponding disk 16. On the side of the flowpath 10, the inner casing 4 is provided with relief 20 forming labyrinths, on the portions located between the blades 18 and facing the vanes 22, and this relief will minimise parasite leaks inherent to functional clearances between the fixed and mobile parts.

#There are vanes 22 anchored to the outer casing 8 through their base 24, between the blades 18. The vanes 22 are distributed on a section of the outer casing 8, so as to form stators 26.