Airfoil portion of a rotor blade or guide vane of a turbo-machine

Abstract

An airfoil portion including an outer wall that defines a cavity for receiving cooling air. The airfoil portion includes a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, and a concave pressure side. At least one insert disposed within the cavity is configured to initially receive at least a portion of the cooling air entering the chamber of the insert and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall of the airfoil portion. The insert further includes a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto. A portion of the cooling air exits the airfoil portion through a plurality of film cooling apertures formed through the outer wall. A main insert includes at least one additional insert which is inserted from the outside and transferred into the cavity at an intermediate position, and then moved in direction to the trailing edge and fixed to predetermined position The additional insert forms the size of the trailing edge channel inlet at the end of the main insert.

1 . An airfoil portion of a rotor blade or guide vane of a turbomachinery; the airfoil portion comprising an outer wall that defines a cavity for receiving cooling air, the airfoil portion comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and at least one insert disposed within the cavity that is configured to initially receive at least a portion of the cooling air entering the chamber of the insert and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall of the airfoil portion, the insert further having a configuration that generally conforms to the contour of the outer wall of the chamber, wherein a portion of the cooling air exits the airfoil portion through a plurality of film cooling apertures formed through the outer wall and/or a portion of the cooling fluid exits the airfoil at the trailing edge, wherein at least one main insert comprising at least one additional insert, wherein the additional insert is fixed to a final predetermined position into the cavity, wherein the additional insert forms the contour of the trailing edge or leading edge with respect to the main insert. 
     
     
         2 . The airfoil portion according to  claim 1 , wherein the additional insert  200  is provided with a transversally elasticity or with fixing means for a form-fit connection with respect to the main insert. 
     
     
         3 . An airfoil portion of a rotor blade or guide vane of a turbomachinery, the airfoil portion comprising an outer wall that defines a cavity for receiving cooling air, the airfoil portion comprising a leading edge that resides in an upstream direction, a trailing edge that resides in a downstream direction, a convex suction side, a concave pressure side, and at least one insert disposed within the cavity that is configured to initially receive at least a portion of the cooling air entering the chamber of the insert and direct the cooling air through a plurality of insert apertures to cool the inner surface of the outer wall of the airfoil portion, the insert further having a configuration that generally conforms to the contour of the outer wall of the chamber but in spaced relation thereto, wherein a portion of the cooling air exits the airfoil portion through a plurality of film cooling apertures formed through the outer wall and/or a portion of the cooling fluid exits the airfoil at the trailing edge, wherein at least one main insert comprising at least one additional insert which forms the contour of the trailing edge cavity at the end of the main insert and/or at least one main insert comprising at least one additional insert which form the contour of the leading edge cavity at the initiation of the main insert. 
     
     
         4 . The airfoil portion according to  claim 3 , wherein the additional insert consists of a structured unitary body. 
     
     
         5 . The airfoil portion according to  claim 3 , wherein at least one main insert comprising at least one additional insert and/or a multiple insert configuration through the internal side of the chamber, wherein the multiple insert configuration forming sub-cavities with respect to the main insert. 
     
     
         6 . The airfoil portion according to  claim 5 , wherein at least two sequentially dispose sub-cavities through the internal side of the main insert reusing the same cooling medium and operating as sequential or quasi-sequential cooling. 
     
     
         7 . The airfoil portion according to  claim 1 , wherein the cavity within the airfoil portion comprises at least one main insert or multiple main inserts and/or at least one or a combination of additional inserts. 
     
     
         8 . The airfoil portion according to  claim 1 , wherein main and/or additional inserts extend to radially or quasi-radially and/or transversally or quasi-transversally direction of the airfoil portion. 
     
     
         9 . The airfoil portion according to  claim 1 , wherein main and/or additional inserts are sectioned and having different shapes or profiles along one or more orientations of the airfoil portion. 
     
     
         10 . The airfoil portion according to  claim 9 , wherein different shapes correspond to a regular or irregular triangular, quadrangular, pentagonal, tapered body. 
     
     
         11 . The airfoil portion according to  claim 1 , wherein a supply channel extends through the interior of the airfoil portion in the flow direction, through which cooling fluid flows. 
     
     
         12 . The airfoil portion according to  claim 1 , wherein a pin fin channel extends from the supply channel along the center line of the airfoil toward the trailing edge of the airfoil portion and opening at the trailing edge to the exterior of the airfoil portion. 
     
     
         13 . The airfoil portion according to  claim 1 , wherein a plurality of gap pin fins projecting from a pair of opposing inner walls that constitute the pin fin channel at a region at the supply channel side of the pin fin channel and form a gap there between extending in the flow direction of the airfoil portion. 
     
     
         14 . The airfoil portion according to  claim 1 , wherein pin fins are in connection with the pair of opposing inner walls at a region at the trailing edge side of a pin fin channel. 
     
     
         15 . The airfoil portion according to  claim 1 , wherein at least one partition portion is disposed in the gap to decrease the area of the channel of the cooling fluid at the region at the supply channel side of a pin fin channel. 
     
     
         16 . The airfoil portion according to  claim 1 , wherein the airfoil portion features in radially or quasi-radially direction with respect to the axis of the turbomachinery a pronounced or swirled or tailored aerodynamic profile. 
     
     
         17 . The airfoil portion according to  claim 1 , wherein the assembling of the airfoil includes:
 at least one additional insert which is inserted from the outside and transferred into the cavity at an intermediate position, and then is moved in direction to the trailing edge or leading edge and is fixed to final predetermined position, or the additional insert is inserted from the underside of the airfoil portion or the additional insert is an element of the cavity of the airfoil portion and subsequently the additional insert is moved in the direction of the trailing edge or leading edge and is fixed to final predetermined position.