Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades

Abstract

A turbojet vane, in particular a compressor guide vane, characterized in that the vane comprises the following elements: an elongate one-piece front portion ( 2 ) cut out from a pultruded section member comprising fibers bonded together by resin and forming a leading edge; an elongate one-piece rear portion ( 3 ) cut out from a pultruded section member comprising fibers bonded together by resin and forming a trailing edge; and a skin ( 5 ) based on resin-impregnated fibers extending between the leading edge and the trailing edge in order to form side faces of the vane and covering at least zones ( 6, 7 ) of the leading edge ( 2 ) and of the trailing edge ( 3 ); these elements being assembled together by hot compaction.

1 . A turbojet vane, in particular a compressor guide vane, characterized in that the vane comprises the following elements:
 an elongate one-piece front portion ( 2 ) cut from a pultruded section member comprising fibers bonded together by resin and forming a leading edge;   an elongate one-piece rear portion ( 3 ) cut from a pultruded section member comprising fibers bonded together by resin and forming a trailing edge; and   a skin ( 5 ) based on resin-impregnated fibers extending between the leading edge and the trailing edge in order to form side faces of the vane and covering at least zones ( 6 ,  7 ) of the leading edge ( 2 ) and of the trailing edge ( 3 );   these elements being assembled together by hot compaction.   
     
     
         2 . A turbojet vane according to  claim 1 , wherein the resin impregnating the skin ( 5 ) is a thermoplastic resin. 
     
     
         3 . A turbojet vane according to  claim 1 , wherein the resin impregnating the leading edge and/or the trailing edge is a thermoplastic resin. 
     
     
         4 . A turbojet vane according to  claim 1 , wherein the leading edge and/or the trailing edge is/are obtained by pultrusion with fibers being placed obliquely. 
     
     
         5 . A turbojet vane according to  claim 1 , wherein the leading edge ( 2 ) and the trailing edge ( 3 ) are connected to each other by reinforcements ( 22 ) extending in the vicinity of the ends of said edges. 
     
     
         6 . A turbojet vane according to  claim 1 , including a core-forming central portion ( 4 ) arranged between the leading edge ( 2 ) and the trailing edge ( 3 ). 
     
     
         7 . A turbojet vane according to  claim 6 , wherein the core ( 4 ) has free ends that are reinforced by inserting short fibers and thermoplastic resin ( 22 ) in a cavity formed by the skin and the core ( 4 ). 
     
     
         8 . A turbojet vane according to  claim 6 , wherein the core ( 4 ) has free ends that are reinforced by folding over portions of the skin ( 5 A,  5 B) on said ends. 
     
     
         9 . A turbojet vane according to  claim 6 , wherein the leading edge ( 2 ) and the trailing edge ( 3 ) present extensions ( 10 ,  11 ,  12 ,  13 ) that project from the core ( 4 ) from at least one end of the vane ( 1 ) in order to carry attachment means ( 14 ,  15 ,  16 ,  17 ) for attaching the vane ( 1 ) to a casing ( 20 ) of the turbojet. 
     
     
         10 . A turbojet vane according to  claim 9 , wherein the attachment means ( 14 ,  15 ,  16 ,  17 ) for attaching the vane to a casing are made directly in the extensions ( 10 ,  11 ,  12 ,  13 ). 
     
     
         11 . A turbojet vane according to  claim 6 , wherein the leading edge ( 2 ) and the trailing edge ( 3 ) are connected together by reinforcements ( 22 ) extending in the vicinity of the ends of said edges, the core ( 4 ) and the reinforcements being made as a single piece of plastics resin, incorporating short fibers. 
     
     
         12 . A turbojet including a plurality of vanes according to  claim 1 , wherein each vane is fastened to at least one casing in such a manner that the attachment means of the vane ( 14 ,  15 ,  16 ,  17 ) co-operate with complementary attachment means ( 21 ,  30 ) of the casing. 
     
     
         13 . A turbojet according to  claim 12 , wherein the attachment means ( 21 ) of the casing comprise at least one peripheral rail ( 21 ) having the ends ( 24 ) of fastener elements ( 23 ) inserted therein, the fastener elements having opposite ends fastened to the attachment means ( 14 ,  15 ,  16 ,  17 ) carried by the leading or trailing edges ( 2 ,  3 ) of the vane ( 1 ). 
     
     
         14 . A turbojet according to  claim 12 , wherein the attachment means ( 30 ) of the casing comprise a peripheral angle bar ( 30 ) having the extensions of the leading or trailing edges ( 2 ,  3 ) fastened directly thereto. 
     
     
         15 . A turbojet according to  claim 12 , wherein the attachment means ( 21 ,  30 ) of the casing are obtained by pultrusion and impregnated with thermoplastic resin, and are assembled to the casing by hot compaction.