Arrangement for providing heat to a portion of a component

Abstract

An arrangement 10 for providing thermal energy to a portion 16 of a component 14 of a gas turbine engine while the component 14 is forming, wherein the component 14 is substantially elongate in a first direction 28 and the portion 16 extends from the component 14 in a second direction 38 , substantially perpendicular to the first direction 28 , and comprises a first surface area component 32 oriented in the first direction 28 . The arrangement 10 further comprising an elongate member 18 , connected to the portion 16 for heating the portion 16 , wherein the elongate member 18 comprises a second surface area component 36 , oriented in the second direction 38 , wherein the second surface area component 36 of the elongate member 18 is greater than the first surface area component 32 of the portion 16.

1 . An arrangement for providing heat to a portion of a component while the component is forming, wherein the component is substantially elongate in a first direction and the portion extends from the component in a second direction, substantially perpendicular to the first direction, and comprises a first surface area component oriented in the first direction; 
 the arrangement further comprising an elongate member, connected to the portion for heating the portion, wherein the elongate member comprises a second surface area component, oriented in the second direction, wherein the second surface area component of the elongate member is greater than the first surface area component of the portion.    
   
   
       2 . An arrangement as claimed in  claim 1 , wherein the portion further comprises a third surface area component, oriented in the second direction and has an area less than the first surface area component.  
   
   
       3 . An arrangement as claimed in  claim 2 , wherein the combined surface area of the second surface area component and the third surface area component is greater than the area of the first surface area component.  
   
   
       4 . An arrangement as claimed in  claim 1 , further comprising a heat source for providing thermal energy to the component.  
   
   
       5 . An arrangement as claimed in  claim 4 , wherein the heat source annularly surrounds the component and is oriented, substantially perpendicular to the first direction.  
   
   
       6 . An arrangement as claimed in  claim 4 , wherein the heat source radiates electromagnetic energy.  
   
   
       7 . An arrangement as claimed in  claim 1 , wherein the portion is a seal fin of a turbine blade.  
   
   
       8 . An arrangement as claimed in  claim 1 , wherein the portion is a platform of a turbine blade.  
   
   
       9 . An arrangement as claimed in  claim 1 , wherein the cross sectional area of the elongate member increases with distance from where it joins the portion.  
   
   
       10 . An arrangement as claimed in  claim 1 , wherein the elongate member additionally provides material to the portion, while the portion is forming.  
   
   
       11 . An arrangement as claimed in  claim 1 , wherein the elongate member is removed from the portion after the component has formed.  
   
   
       12 . An arrangement as claimed in  claim 1 , wherein the component is one of a blade, nozzle guide vane and a seal segment for a turbine assembly of a gas turbine engine.  
   
   
       13 . A method for use in forming a component of a gas turbine engine, wherein the component has a portion that extends from the component in a second direction, substantially perpendicular to a first direction, and an elongate member is connected to the portion for heating the portion, the method comprising: moving the component in the first direction; and heating the elongate member as the component moves so that there is net thermal energy input for the portion.  
   
   
       14 . A method as claimed in  claim 13 , further comprising removing the elongate member from the component.  
   
   
       15 . A component produced by the method as claimed in  claim 13.