Gas turbine engine component

Abstract

In a gas turbine engine at least one vanes is made of a composite material and an end part of the vane is fastened to the ring element by at least a first bracket member arranged in a corner region formed by the vane and a ring element. The first bracket member is fastened to the vane by a first fastening device arranged in association with a first hole extending through the vane. The first bracket member is fastened to the ring element by a second fastening device arranged in association with a second hole extending through the ring element. An opening is arranged in the ring element. A second bracket member at least partly has an angular cross section. The second, angled bracket member is arranged through the opening such as to be positioned on an opposite side of both the vane and the ring element in relation to the first bracket member. The second, angled bracket member is fastened to the first bracket member by the first and second fastening devices.

1 . Gas turbine engine component, comprising
 a ring element and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element,   wherein at least one of the vanes is made of a composite material and wherein an end part of the at least one composite vane is fastened to the ring element by means of at least a first bracket member arranged in a corner region formed by the composite vane and the ring element,   wherein the first bracket member is fastened to the composite vane by means of a first fastening device arranged in association with a first hole extending through the composite vane, and wherein the first bracket member is fastened to the ring element by means of a second fastening device arranged in association with a second hole extending through the ring element, wherein an opening is arranged in the ring element and that the component comprises a second bracket member that at least partly has an angular cross section,   wherein the second, angled bracket member is arranged through the opening such as to be positioned on an opposite side of both the composite vane and the ring element in relation to the first bracket member, and   wherein the second, angled bracket member is fastened to the first bracket member by means of the first and second fastening devices.   
     
     
         2 . Gas turbine engine component according to  claim 1 , wherein a first insertion member is arranged in the first hole, wherein the relative dimensions of the first insertion member and the first hole are such as to provide a tight radial fit for the first insertion member in the first hole, and wherein the first insertion member is fixed in relation to both the first and the second bracket member. 
     
     
         3 . Gas turbine engine component according to  claim 1 , wherein the first fastening device is configured to press the first and second bracket members towards each other from opposite sides of the composite vane when tightened, wherein the component is arranged in such a way that each of the first and second bracket members exerts a pressure directly or indirectly onto its corresponding side of the composite vane when the first fastening device is tightened. 
     
     
         4 . Gas turbine engine component according to  claim 2 , wherein the first fastening device is configured to press the first and second bracket members towards each other from opposite sides of the composite vane when tightened, wherein the component is arranged in such a way that each of the first and second bracket members exerts pressure directly or indirectly onto its corresponding side of the composite vane when the first fastening device is tightened, and the component is arranged in such a way that each of the first and second bracket members exerts a pressure directly or indirectly onto opposite sides of the first insertion member, as seen in an axial direction of the first hole, when the first fastening device is tightened. 
     
     
         5 . Gas turbine engine component according to  claim 2 , wherein the first insertion member extends in the first hole along an axial direction thereof. 
     
     
         6 . Gas turbine engine component according to  claim 2 , wherein the first insertion member is a bushing member. 
     
     
         7 . Gas turbine engine component according to  claim 6 , wherein the first fastening device comprises a first fastening member that extends in an axial direction through the first hole and that the bushing member extends at least partly around and along the fastening member. 
     
     
         8 . Gas turbine engine component according to  claim 1 , wherein a second insertion member is arranged in the second hole,
 wherein the relative dimensions of the second insertion member and the second hole are such as to provide a tight radial fit for the second insertion member in the second hole, and   wherein the second insertion member is fixed in relation to both the first and the second bracket member.   
     
     
         9 . Gas turbine engine component according to  claim 1 , wherein the second fastening device is configured to press the first and second bracket members towards each other from opposite sides of the ring element when tightened, wherein the component is arranged in such a way that each of the first and second bracket members exerts a pressure directly or indirectly onto its corresponding side of the ring element when the second fastening device is tightened. 
     
     
         10 . Gas turbine engine component according to  claim 8 , wherein the second fastening device is configured to press the first and second bracket members towards each other from opposite sides of the ring element when tightened, wherein the component is arranged in such a way that each of the first and second bracket members exerts a pressure directly or indirectly onto its corresponding side of the ring element when the second fastening device is tightened, and the component is arranged in such a way that each of the first and second bracket members exerts a pressure directly or indirectly onto opposite sides of the second insertion member, as seen in an axial direction of the second hole, when the second fastening device is tightened. 
     
     
         11 . Gas turbine engine component according to  claim 8 , wherein the second insertion member extends in the second hole along an axial direction thereof. 
     
     
         12 . Gas turbine engine component according to  claim 8 , wherein the second insertion member is a bushing member. 
     
     
         13 . Gas turbine engine component according to  claim 12 , wherein the second fastening device comprises a second fastening member that extends in an axial direction through the second hole and that the second bushing member extends at least partly around and along the fastening member. 
     
     
         14 . Gas turbine engine component according to  claim 8 , wherein the second insertion member forms an integrated part of the first bracket member. 
     
     
         15 . Gas turbine engine component according to  claim 1 , wherein the first bracket member has a third hole and a fourth hole and is arranged such that the third and fourth holes coincide with the first and second holes, respectively. 
     
     
         16 . Gas turbine engine component according to  claim 15 , wherein the third hole is arranged in a first part of the first bracket member, which first part extends in a plane that is substantially in parallel with a radial direction of the ring element, and that the fourth hole is arranged in a second part of the first bracket member, which second part extends in a plane that is substantially in parallel with a circumferential direction of the ring element. 
     
     
         17 . Gas turbine engine component according to  claim 1 , wherein the second, angled bracket member is provided with a fifth hole and a sixth hole, wherein the fifth hole coincides with the first hole and the sixth hole coincides with the second hole. 
     
     
         18 . Gas turbine engine component according to  claim 17 , wherein the fifth hole is arranged in a radially directed part of the second, angled bracket member, which radial part extends in a plane that is substantially in parallel with a radial direction of the ring element, and that the sixth hole is arranged in a circumferentially directed part of the second, angled bracket member, which circumferentially part extends in a plane that is substantially in parallel with a circumferential direction of the ring element. 
     
     
         19 . Gas turbine engine component according to  claim 1 , wherein the first and second bracket members are made of a metallic material. 
     
     
         20 . Gas turbine engine component according to  claim 2 , wherein the first insertion member is made of a metallic material. 
     
     
         21 . Gas turbine engine component according to  claim 8 , wherein the second insertion member is made of a metallic material. 
     
     
         22 . Gas turbine engine component according to  claim 2 , wherein the tight radial fit corresponds to a radial play of <0.1 mm. 
     
     
         23 . Gas turbine engine component according to  claim 1 , wherein the component comprises an inner ring element and an outer ring element connected by the plurality of circumferentially spaced load carrying vanes. 
     
     
         24 . Gas turbine engine component according to  claim 1 , wherein the component is configured to define a gas flow in a gas turbine engine, such as a turbo-jet engine. 
     
     
         25 . Gas turbine engine component according to  claim 1 , wherein the component comprises a further set of bracket members, fastening devices, holes and opening according to  claim 1  for fastening the end part of the at least one composite vane to the ring element, wherein the further set is positioned at a distance from the set according to  claim 1  as seen in an axial direction of the ring element. 
     
     
         26 . Gas turbine engine component according to  claim 24 , wherein a further bracket member ( 51 ) of the further set, which further bracket member corresponds to the first bracket member, is arranged on an opposite side of the composite vane in relation to the first bracket member. 
     
     
         27 . Gas turbine engine, wherein it comprises a component according to  claim 1 .