Gas-Turbine Aircraft Engine With Structural Surface Cooler

Abstract

The present invention relates to a gas-turbine aircraft engine with a core engine surrounded by a bypass duct, with a substantially annular cooling element being provided in the area of a radially inner wall of the bypass duct downstream of stator vanes of the bypass duct.

1 . Gas-turbine aircraft engine with a core engine surrounded by a bypass duct, with a substantially annular cooling element being provided in the area of a radially inner wall of the bypass duct downstream of stator vanes of the bypass duct. 
     
     
         2 . Gas-turbine aircraft engine in accordance with  claim 1 , characterized in that the cooling element is designed as a surface cooler. 
     
     
         3 . Gas-turbine aircraft engine in accordance with  claim 1 , characterized in that the cooling element is arranged downstream of a rear area of a radially inner flange of a stator vane ring. 
     
     
         4 . Gas-turbine aircraft engine in accordance with  claim 3 , characterized in that the stator vanes are connected to the cooling element for heat transmission. 
     
     
         5 . Gas-turbine aircraft engine in accordance with  claim 1 , characterized in that the cooling element is provided with cooling ducts extending in the circumferential direction. 
     
     
         6 . Gas-turbine aircraft engine in accordance with  claim 1 , characterized in that the cooling element is provided as an extruded section bent into shape. 
     
     
         7 . Gas-turbine aircraft engine in accordance with Claim  1 , characterized in that the cooling element on its radially outer side is provided with cooling ribs.