US 5,472,314 AGranted

Variable camber turbomachine blade having resilient articulation

AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."

InventorsJean-Claude L. Delonge, Claude J. A. Loudet, Gerard R. E. R. Vermont

Life of this patent

Estimating the term…

Loading patent…

Abstract

A variable camber vane for a turbomachine comprises leading and trailing edge parts, at least one of which is pivotable relative to the other, and a resilient joining part inserted into a space provided between the leading and trailing edge parts, the joining part being formed by a block of resilient material which is bonded to the leading and trailing edge parts and which ensures the continuity of the intrados and extrados faces of the vane to permit an even flow of fluid along the vane. The vane may also include means for enabling a cooling or heating fluid to flow in the leading and trailing edge parts, and a plurality of ducts in the resilient joining part establishing communication between the fluid flow means of the leading and trailing edge parts.

Claims5

Dependent claims

A variable camber vane for a turbomachine, said vane having an intrados face and an extrados face and comprising

leading edge part,
trailing edge part disposed relative to said leading edge part to define a space therebetween,
means for mounting at least one of said edge parts for pivotal movement relative to the other of said edge parts about an axis of rotation in the direction of the height of said vane, and
a resilient joining part within said space between said leading edge part and said trailing edge part,
said joining part comprising a block of resilient material firmly secured on one side to said leading edge part and on its opposite side to said trailing edge part,
said block of resilient material, said leading edge part and said trailing edge part each having first and second flanks,
said first flank of said block forming a continuation of said first flanks of said leading and trailing edge parts and defining therewith said intrados face of said vane, and
said second flank of said block forming a continuation of said second flanks of said leading and trailing edge parts and defining therewith said extrados face of said vane,
wherein said joining part fills said space between said leading edge part and said trailing edge part.

6 more elements

Dependencies are inferred from the claim text.

Facts

Application: 08/271,634Filed 7 Jul 1994
Priority: FR 93 083167 Jul 1993
Granted: 5 Dec 1995
Term ends: Not estimatedThe source records don’t support an estimate.

Classification7 codes

F01D 5/187
Hollow blades, i.e. blades with cooling or heating channels or cavities ; Heating, heat-insulating or cooling means on blades: convection cooling
F01D 5/148
Form or construction: blades with variable camber, e.g. by ejection of fluid
F01D 17/162
By means of nozzle vanes: for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
F01D 25/02
Component parts, details, or accessories, not provided for in, or of interest apart from, other groups: de-icing means for engines having icing…