Vane assembly configured for turning a flow in a gas turbine engine, a stator component comprising the vane assembly, a gas turbine and an aircraft jet engine

Abstract

A vane assembly configured for turning a flow in a gas turbine engine includes a stationary main guide vane and an additional guide vane, wherein a leading edge of the additional guide vane is positioned upstream of a leading edge of the main guide vane and wherein the additional guide vane extends a distance along the main guide vane towards a trailing edge of the main guide vane forming a passageway between the additional guide vane and the main guide vane.

1 . Vane assembly ( 206 ) configured for turning a flow in a gas turbine engine ( 100 ) comprising a stationary main guide vane ( 208 ) and an additional guide vane ( 210 ), wherein a leading edge ( 318 ) of the additional guide vane ( 210 ) is positioned upstream of a leading edge ( 310 ) of the main guide vane ( 208 ) and wherein the additional guide vane ( 210 ) extends a distance along the main guide vane ( 208 ) towards a trailing edge ( 312 ) of the main guide vane ( 208 ) forming a passageway ( 322 ) between the additional guide vane ( 210 ) and the main guide vane ( 208 ). 
   
   
       2 . Vane assembly according to  claim 1 , wherein the additional guide vane ( 210 ) is positioned relative to the main guide vane ( 208 ) so that the passageway ( 322 ) becomes more narrow in a downstream direction. 
   
   
       3 . Vane assembly according to  claim 1  or  2 , wherein the additional guide vane ( 210 ) is positioned relative to the main guide vane ( 208 ) so that the passageway ( 322 ) continuously narrows down from an upstream opening ( 324 ) of the passageway to a downstream opening ( 326 ). 
   
   
       4 . Vane assembly according to any preceding claim, wherein the additional guide vane ( 210 ) is positioned relative to the main guide vane ( 208 ) so that the passageway ( 322 ) is shaped as a nozzle. 
   
   
       5 . Vane assembly according to any preceding claim, wherein the additional guide vane ( 210 ) has an at least partly curved shape. 
   
   
       6 . Vane assembly according to  claim 5 ,
 wherein a first, upstream portion of a suction side of the additional guide vane ( 210 ) extending from a leading edge of the additional guide vane ( 210 ) is substantially straight and that a second, downstream portion of the suction side of the additional guide vane ( 210 ) is curved.   
   
   
       7 . Vane assembly according to  claim 6 ,
 wherein the first, upstream portion of the suction side of the additional guide vane ( 210 ) extends over at least 50% of the chord of the additional guide vane.   
   
   
       8 . Vane assembly according to  claim 6 ,
 wherein the first, upstream portion of the suction side of the additional guide vane ( 210 ) extends over about 70% of the chord of the additional guide vane.   
   
   
       9 . Vane assembly according to any of  claims 5 - 8 ,
 wherein a concave part of the additional guide vane ( 210 ) defines one side of the passageway.   
   
   
       10 . Vane assembly according to any preceding claim, wherein the main guide vane ( 208 ) has an at least partly curved shape. 
   
   
       11 . Vane assembly according to any preceding claim, wherein a concave part of the additional guide vane ( 210 ) is arranged along a convex part of the main guide vane ( 208 ), wherein the passageway is defined therebetween. 
   
   
       12 . Vane assembly according to any preceding claim, wherein a leading edge of the additional guide vane ( 210 ) has an elliptic cross sectional shape. 
   
   
       13 . Vane assembly according to any preceding claim, wherein the main guide vane ( 208 ) is configured to turn an incoming flow. 
   
   
       14 . Vane assembly according to any preceding claim, wherein the additional guide vane ( 210 ) is configured to turn an incoming flow. 
   
   
       15 . Vane assembly according to any preceding claim, wherein the main guide vane ( 208 ) has the shape of an airfoil in cross section. 
   
   
       16 . Vane assembly according to any preceding claim, wherein the additional guide vane ( 210 ) has the shape of an airfoil in cross section. 
   
   
       17 . Vane assembly according to  claim 15  and  16 , wherein a pressure side of the additional guide vane ( 210 ) faces a suction side of the main guide vane ( 208 ), wherein the passageway is defined therebetween. 
   
   
       18 . Vane assembly according to any preceding claim, wherein a trailing edge of the additional guide vane ( 210 ) is arranged upstream of the trailing edge of the main guide vane ( 208 ). 
   
   
       19 . Vane assembly according to any preceding claim, wherein a trailing edge of the additional guide vane ( 210 ) is arranged upstream of a point halfway of the chord of the main guide vane ( 208 ). 
   
   
       20 . Vane assembly according to any preceding claim, wherein the additional guide vane ( 210 ) has a substantially smaller thickness to chord ratio than the main guide vane ( 208 ). 
   
   
       21 . Vane assembly according to any preceding claim, wherein the main guide vane ( 208 ) is structurally bearing. 
   
   
       22 . Vane assembly according to any preceding claim, wherein the main guide vane ( 208 ) is adapted for housing service components. 
   
   
       23 . Vane assembly according to any preceding claim, wherein the additional guide vane ( 210 ) is stationary. 
   
   
       24 . Stator component comprising a plurality of said vane assemblies according to any preceding claim, wherein the main guide vanes ( 208 ) are circumferentially spaced. 
   
   
       25 . A gas turbine engine comprising a stator component according to  claim 24 . 
   
   
       26 . An aircraft jet engine comprising a stator component according to  claim 24 .