Patent ID: 9702259
Date: 2017-07-11
CPC Classifications: F01D,F04D,F05D

Claim:
1. A sectorized compressor guide vane assembly for a turbomachine, comprising: assembled sectors that form two concentric outer and inner shell rings, said concentric outer and inner shell rings having front and rear transverse faces; and vanes arranged between the concentric outer and inner shell rings, each vane comprising a leading edge closer to the front transverse face of the outer and inner shell rings than the rear transverse face of the outer and inner shell rings and a trailing edge closer to the rear transverse face of the outer and inner shell rings than the front transverse face of the outer and inner shell rings, the outer shell ring externally includes means of attachment to an external casing for housing the sectors, wherein the means of attachment are axially offset from the rear transverse face of the outer shell ring and is configured to absorb static forces between the external casing and the guide vane assembly, the means of attachment to the external casing comprising, in relation to a direction of flow passing through the vanes, a front curved peripheral engagement rim situated at the front transverse face of the outer shell ring of the sectors, and a rear curved peripheral engagement rim offset from the rear transverse face of the outer shell ring, the rear curved peripheral engagement rim and an end portion of the rear curved peripheral engagement rim are provided so as to be situated projecting substantially in a center of the vanes between the leading and trailing edges thereof, both curved peripheral engagement rims being designed to cooperate with slots of the external casing for maintaining the guide vane assembly.