Flow guiding device and turbo-engine with at least one flow guiding device

Abstract

A flow guiding device in a turbomachine with at least one rotor module that is arranged on a shaft is provided. The rotor module has at least two rotor discs between which respectively one rotor cavity is arranged. The rotor cavities are connected to each other in an air-guiding manner for an airflow by means of openings inside the rotor discs and at least one pressure sink device for creating a localized negative pressure is arranged inside the last rotor cavity as viewed in the main flow direction of the turbomachine.

1 . A flow guiding device in a turbomachine with at least one rotor module, which is arranged on a shaft, wherein the rotor module has at least two rotor discs between which respectively one rotor cavity is arranged,
 wherein the rotor cavities are connected to each other in an air-guiding manner for an airflow by means of openings inside the rotor discs, and in that at least one pressure sink device for creating a localized negative pressure is arranged inside the last rotor cavity as viewed in the main flow direction of the turbomachine.   
     
     
         2 . The flow guiding device according to  claim 1 , wherein the airflow that enters the rotor cavities can be guided through the openings in the direction of the at least one pressure sink device. 
     
     
         3 . The flow guiding device according to  claim 1 , wherein the rotor module is configured as a compressor module, and wherein the airflow can be guided from the flow channel of the compressor module into at least one rotor cavity through at least one inlet opening. 
     
     
         4 . The flow guiding device according to  claim 1 , wherein the rotor discs have respectively at least two openings that are arranged in an axisymmetric manner with respect to the shaft of the turbomachine. 
     
     
         5 . The flow guiding device according to  claim 1 , wherein the rotor discs respectively have a material reinforcement in the area of the openings. 
     
     
         6 . The flow guiding device according to  claim 5 , wherein the material reinforcement is configured as a ring and/or a web that surrounds the openings. 
     
     
         7 . The flow guiding device according to  claim 1 , wherein the pressure sink device at least has vortex rectifiers and/or a means for creating a localized negative pressure by means of a targeted acceleration of the airflow. 
     
     
         8 . The flow guiding device according to  claim 1 , wherein the airflow can be guided from the pressure sink device into another part of the turbomachine, in particular a turbine module. 
     
     
         9 . The flow guiding device according to  claim 1 , wherein in at least one rotor cavity a device for deflecting a radial stream of air inside the at least one rotor cavity is arranged, wherein the deflected air can be guided axially in the direction of the pressure sink device. 
     
     
         10 . The flow guiding device according to  claim 1 , wherein the turbomachine is configured as an aircraft engine. 
     
     
         11 . A turbomachine, in particular an aircraft engine, with at least one flow guiding device according to  claim 1 .