Array of components

Abstract

A support element 22 is fitted between adjacent vanes 8, 14 in a gas turbine engine, in order to suppress vibrations in the vanes 8, 14 . The support element 22 comprises a body portion 24 and pad portions 38, 40 which contact the vanes 8, 14 over a wide area to restrain displacement of the vanes 8, 14 while minimising overstressing.

1 . An array of vanes for a gas turbine engine, the array being an annular array disposed about a central axis, and the vanes being assembled in packs, wherein each pack comprises two rows of vanes, the vanes of each pack being supported at at least one end by a common end support so as to be spaced apart from one another and which, in use, are subjected to excitation inputs which induce vibration in the vanes, a support element being disposed between two adjacent vanes in each row, the support element comprising respective body portions disposed between the adjacent vanes in each row and a pad portion which extends laterally from each body portion, the pad portion having a contact surface which contacts a surface of one of the adjacent components, characterised in that a bridge region is provided between the body portion regions. 
   
   
       2 . An array as claimed in  claim 1 , characterised in that the body portion regions are offset with respect to each other in a direction (G) extending between the adjacent vanes. 
   
   
       3 . An array as claimed in  claim 1 , characterised in that the pad portion is one of two pad portions disposed at opposite sides of the body portion, the contact surface of each pad portion contacting a respective one of the adjacent vanes. 
   
   
       4 . An array as claimed in  claim 1 , characterised in that the body portion comprises a central web, the or each pad portion comprising a flange extending from an edge of the web. 
   
   
       5 . An array as claimed in  claim 4 , characterised in that the central web is curved about an axis extending parallel to the direction (G) extending between the adjacent vanes. 
   
   
       6 . An array as claimed in  claim 1 , characterised in that the support element is secured to at least one of the adjacent vanes. 
   
   
       7 . An array as claimed in  claim 6 , characterised in that the support element is secured to the adjacent vane by bonding at the contact surface. 
   
   
       8 . An array as claimed in  claim 6 , characterised in that the support element is secured to the adjacent vane by means of a projection on the support element which engages an aperture in the vane. 
   
   
       9 . An array as claimed in  claim 1 , characterised in that the vanes extend substantially radially with respect to the axis. 
   
   
       10 . An array as claimed in  claim 1 , characterised in that the vanes of each pack are interconnected by a connecting element at at least one radial end. 
   
   
       11 . An array as claimed in  claim 10 , characterised in that the support element is disposed between adjacent vanes of a common pack. 
   
   
       12 . An array as claimed in  claim 1 , characterised in that the support element is disposed between adjacent vanes of adjacent packs. 
   
   
       13 . An array as claimed in  claim 1 , characterised in that the support element is disposed substantially midway between the ends of the vanes. 
   
   
       14 . An array as claimed in  claim 1 , characterised in that the body portion has an aerodynamic profile conforming to fluid flow in use between the vanes. 
   
   
       15 . An array as claimed in  claim 1 , characterised in that each pad portion has an aerodynamic flow surface on a side of the pad portion opposite the contact surface. 
   
   
       16 . An array as claimed in  claim 1  characterised in that the array has a plurality of support elements, and the support elements are disposed between some only of the vanes of the array. 
   
   
       17 . A support element for use in an array of vanes for a gas turbine engine in accordance with  claim 1 .