Turbomachine compressor guide vanes assembly
View Patent ↗A sectorized turbomachine compressor guide vanes assembly includes assembled sectors forming two concentric shell rings, one outer and one inner, between which vanes are arranged with their leading and trailing edges near transverse faces of the shell rings, and of which an outer shell ring externally includes an attachment mechanism to an external casing that houses the sectors. The attachment mechanism is axially offset from the rear transverse face of the shell ring to be located, in projection, in alignment with the vanes between the leading and trailing edges thereof.
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.
2. A guide vane assembly according to claim 1 , wherein the rear curved peripheral rim extends continuously or discontinuously over all the sectors.
3. A guide vane assembly according to claim 1 , wherein the center of the vanes presents a thickest portion of the vanes.
4. 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, an annular flange projecting radially from the outer shell ring, provided on a periphery of the outer shell ring and situated projecting directly above the vanes between the leading edge and trailing edge of said vanes,
said annular flange being situated projecting in a center of the leading and trailing edges of the vanes,
the center of the vanes presents a thickest portion of the vanes and the annular flange being situated projecting substantially in a region of said thickest portion, and
said annular flange being provided at regular intervals on its periphery of the outer shell ring with holes so as to fix bolts passing through said holes and to fix to the external casing.
5. A guide vane assembly according to claim 4 , wherein the annular flange has a thickness equal to at most twice a thickness of the outer shell ring.