Installation having a thermal transfer arrangement

Abstract

A gas turbine engine 2 is installed in a nacelle 4 to define a bay 16 which is ventilated by air entering the bay 16 through an intake 27. A partition 28 in the bay 16 includes a permeable wall 34 provided with flow passages 36 which direct the air flow in the bay 16 towards a turbine casing 14. The air flow is emitted from the flow passages 36 as jets 46 to provide impingement cooling of the turbine casing 14.

1 . An installation comprising a component having a means for inducing fluid flow through the component, and a thermal transfer arrangement, the thermal transfer arrangement comprising a chamber which is ventilated in operation of the installation by a forced fluid flow induced by a means different to the means for inducing fluid flow through the component, the chamber being bounded at least partly by a heat transfer surface of the component, a flow passage being disposed within the chamber, which flow passage is oriented to direct at least part of the fluid flow at the heat transfer surface to transfer heat between the fluid and the heat transfer surface. 
     
     
         2 . An installation comprising a component having a means for inducing fluid flow through the component, and a cooling arrangement for cooling the component, the cooling arrangement comprising a chamber which is ventilated in operation of the installation by a forced fluid flow induced by a means different to the means for inducing fluid flow through the component, the chamber being bounded at least partly by a surface of the component, a flow passage being disposed within the chamber, which flow passage is oriented to direct at least part of the fluid flow at the surface of the component, to cool the component. 
     
     
         3 . An installation as claimed in  claim 2 , in which the flow passage is provided in a wall situated within the chamber. 
     
     
         4 . An installation as claimed in  claim 3 , in which the wall extends generally parallel to the heat transfer surface or the surface of the component. 
     
     
         5 . An installation as claimed in  claim 3 , in which the wall is part of a partition which divides the chamber into upstream and downstream compartments, with respect to the direction of fluid flow through the chamber. 
     
     
         6 . An installation as claimed in  claim 3 , in which the flow passage is one of an array of flow passages in the wall. 
     
     
         7 . An installation as claimed in  claim 3 , in which the or each flow passage comprises a hole in the wall. 
     
     
         8 . An installation as claimed in  claim 7 , in which the wall material defining the or each flow passage is inclined to the plane of the wall, thereby to direct fluid passing through the respective flow passage. 
     
     
         9 . An installation as claimed in  claim 3 , in which the wall is provided with louvers, and the or each flow passage comprises a channel defined between adjacent louvers. 
     
     
         10 . An installation as claimed in  claim 9 , in which the or each channel has an inlet aligned substantially with the general direction of fluid flow through the chamber, and an outlet directed towards the heat transfer surface or the surface of the component. 
     
     
         11 . An installation as claimed in  claim 2 , in which the component is a combustion engine, the chamber being defined between the engine and an engine enclosure. 
     
     
         12 . An installation as claimed in  claim 11 , in which the engine is a gas turbine engine and the enclosure is a nacelle, the chamber being annular, and defined between the nacelle and the engine. 
     
     
         13 . An installation as claimed in  claim 12 , when appendant to  claim 3 , in which the wall is part of a partition extending between the engine and the nacelle. 
     
     
         14 . An installation as claimed in  claim 11 , in which the surface to be cooled is a turbine casing of the engine.