Passage channel for a turbomachine and turbomachine

Abstract

A transition duct for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section, including supporting ribs which extend between a radially inner duct wall and a radially outer duct wall and each of which has a profile for deflecting a flow from an inlet area to an outlet area of the transition duct, the supporting ribs each having a profile variation in the area of their trailing edge and/or at least one blow-out opening for blowing out a fluid; also disclosed is a turbomachine having a transition duct of this type.

1 - 12 . (canceled) 
     
     
         13 . A transition duct for a turbomachine for forming a flow channel between an upstream flow cross section and a downstream flow cross section, the transition duct comprising:
 a radially inner duct wall;   a radially outer duct wall; and   supporting ribs extending between the radially inner duct wall and the radially outer duct wall, each supporting rib having a profile for deflecting a flow from an inlet area to an outlet area of the transition duct,   each supporting rib having a profile variation in an area of a trailing edge and/or at least one blow-out opening for blowing out a fluid.   
     
     
         14 . The transition duct as recited in  claim 13  wherein the trailing edge is alternately offset in relation to a suction side and to a pressure side of the supporting rib. 
     
     
         15 . The transition duct as recited in  claim 13  wherein the trailing edge has a wave design in the flow direction. 
     
     
         16 . The transition duct as recited in  claim 13  wherein each supporting rib has the at least one blow-out opening exiting the trailing edge between a suction side and a pressure side of the supporting rib. 
     
     
         17 . The transition duct as recited in  claim 16  wherein the at least one blow-out opening is a longitudinal slot extending from the inner duct wall to the outer duct wall, a suction-side slot area having a wave-shaped design and a diametrically opposed pressure-side slot area being designed without variation. 
     
     
         18 . The transition duct as recited in  claim 17  wherein a suction-side outflow area diametrically opposed to the suction-side slot area has a further wave-shaped design. 
     
     
         19 . The transition duet as recited in  claim 16  wherein the at least one blow-out opening is a longitudinal slot, a pressure-side slot area having a wave-shaped design and a diametrically opposed suction-side slot area being designed without variation. 
     
     
         20 . The transition duct as recited in  claim 19  wherein a pressure-side outflow area diametrically opposed to the pressure-side slot area has a wave-shaped design. 
     
     
         21 . The transition duct as recited in  claim 13  wherein the supporting rib has the blow-out opening exiting on a suction side. 
     
     
         22 . The transition duct as recited in  claim 13  further comprising flow splitter blades situated between the supporting ribs and having a smaller relative profile thickness than the supporting ribs ( 14 ). 
     
     
         23 . The transition duct as recited in  claim 22  wherein the flow splitter blades having a further trailing edge-side profile variation and/or at least one further blow-out opening. 
     
     
         24 . A turbomachine comprising a transition duct as recited  claim 13 . 
     
     
         25 . An aircraft engine comprising the turbomachine as recited in  claim 24 .