Gas turbine engine and variable camber vane system

Abstract

One embodiment of the present invention is a unique variable camber vane system for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and variable camber vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

1 . A variable camber vane system for a gas turbine engine, comprising:
 a first airfoil portion having a first tip portion, a first root portion, a face extending at least partially between the first tip portion and the first root portion, and a groove in the face extending at least partially between the first tip portion and the first root portion, wherein the groove has a groove width;   a second airfoil portion arranged to rotate with respect to the first airfoil portion about a pivot axis, wherein the second airfoil portion includes a second tip portion; a second root portion; and a crown extending at least partially between the second tip portion and the second root portion, wherein the crown includes a crown radius centered about the pivot axis and positioned opposite the groove; and   a seal strip having a seal width greater than the groove width and a rubbing surface opposite the crown radius, wherein the seal strip is at least partially disposed in the groove with an interference fit; and wherein the seal strip is arranged to seal against fluid flow between the first airfoil portion and the second airfoil portion.   
     
     
         2 . The variable camber vane system of  claim 1 , wherein the seal strip is a rigid structure. 
     
     
         3 . The variable camber vane system of  claim 1 , wherein the rubbing surface has a rubbing surface radius the same as the crown radius. 
     
     
         4 . The variable camber vane system of  claim 1 , wherein the crown is formed integrally with the second airfoil portion. 
     
     
         5 . The variable camber vane system of  claim 1 , wherein the face is formed integrally with the first airfoil portion. 
     
     
         6 . The variable camber vane system of  claim 1 , wherein the face is concave and operative to receive the crown therein. 
     
     
         7 . The variable camber vane system of  claim 1 , wherein the first airfoil portion is stationary. 
     
     
         8 . The variable camber vane system of  claim 7 , wherein the first airfoil portion and the second airfoil portion form at least part of an inlet guide vane having a fixed leading edge and a variable trailing edge; wherein the first airfoil portion includes the leading edge; and wherein the second airfoil portion includes the trailing edge. 
     
     
         9 . The variable camber vane system of  claim 7 , wherein the first airfoil portion and the second airfoil portion form at least part of an outlet guide vane having a variable leading edge and a fixed trailing edge; wherein the first airfoil portion includes the leading edge; and wherein the second airfoil portion includes the trailing edge. 
     
     
         10 . A gas turbine engine, comprising:
 at least one of a fan and a compressor having a variable camber vane system, the variable camber vane system including:
 at least two airfoil portions adapted to vary a camber of the variable camber vane system, wherein a first of the airfoil portions includes a groove and a second of the airfoil portions includes a crown having a crown radius; and 
 a seal strip at least partially disposed in the groove with an interference fit, 
   wherein the seal strip includes a rubbing surface opposite the crown radius and operative to seal against fluid flow between the first of the airfoil portions and the second of the airfoil portions.   
     
     
         11 . The gas turbine engine of  claim 10 , wherein the rubbing surface contacts the crown at the crown radius. 
     
     
         12 . The gas turbine engine of  claim 10 , wherein the seal strip is formed of a polymer material. 
     
     
         13 . The gas turbine engine of  claim 12 , wherein the seal strip is formed of at least one of Vespel and Torlon. 
     
     
         14 . The gas turbine engine of  claim 10 , wherein the at least two airfoil portions form an inlet guide vane. 
     
     
         15 . The gas turbine engine of  claim 10 , wherein the at least two airfoil portions form an outlet guide vane. 
     
     
         16 . A gas turbine engine, comprising:
 at least one of a fan and a compressor having a variable camber vane system, the variable camber vane system including:
 at least two airfoil portions adapted to vary a camber of the variable camber vane system, wherein a first of the airfoil portions includes a groove; and wherein a second of the airfoil portions includes a crown having a crown radius; and 
 a seal strip disposed in the groove; wherein the seal strip has a rubbing surface radius preformed thereon and configured for sealing engagement with the crown. 
   
     
     
         17 . The gas turbine engine of  claim 16 , wherein the seal strip is a rigid structure formed of a polymer. 
     
     
         18 . The gas turbine engine of  claim 16 , wherein the crown radius is convex, and wherein the rubbing surface radius is concave. 
     
     
         19 . The gas turbine engine of  claim 16 , wherein the seal strip is fitted in the groove with an interference fit. 
     
     
         20 . The gas turbine engine of  claim 16 , wherein the crown is nested within the first of the airfoil portions opposite the groove.