Combustor cap mounting structure for a turbine engine

Abstract

A mounting structure for mounting a combustor cap in a combustor of a turbine engine includes support struts that are connected between the combustor cap and a concentric combustor cap barrel flange. The support struts may have an airfoil shape to minimize wakes created in a flow of compressed air that is passing over the support struts. Also, the support struts may have an interior passageway that allows a portion of the compressed air to flow though the support strut. The flow of air passing through the support struts may also pass through corresponding vent apertures in the combustor cap barrel flange so that the flow of air passing through the support struts is delivered into a space between the exterior of the combustor cap barrel flange and a forward casing of the combustor.

What is claimed is: 
     
         1 . A combustor cap assembly for a turbine engine, comprising:
 a generally cylindrical combustor cap configured to receive at least one fuel nozzle;   a generally cylindrical combustor cap barrel flange that surrounds an outer circumference of the combustor cap; and   a plurality of support struts that mount the combustor cap to the combustor cap barrel flange and which extend between the outer circumference of the combustor cap and an inner circumference of the combustor cap barrel flange, wherein an interior passageway extends through an interior of each support strut.   
     
     
         2 . The combustor cap assembly of  claim 1 , wherein vent apertures are formed in the combustor cap barrel flange at locations corresponding to where the support struts are attached to the combustor cap barrel flange, and wherein each vent aperture operatively communicates with the interior passageway of a corresponding support strut. 
     
     
         3 . The combustor cap assembly of  claim 2 , wherein the interior passageway in each support strut extends between an entrance aperture located on a side surface of the support strut and an exit aperture that is formed on a portion of the support strut that abuts the combustor cap barrel flange. 
     
     
         4 . The combustor cap assembly of  claim 3 , wherein the entrance aperture of each support strut is located on a leading edge portion of the support strut which is impacted by a flow of compressed air. 
     
     
         5 . The combustor cap assembly of  claim 3 , wherein the support struts are mounted to the combustor cap barrel flange such that a flow of air can pass from the entrance aperture of each support strut, through the interior passageway, out the exit aperture of the support strut and through a corresponding vent aperture of the combustor cap barrel flange to a location adjacent an exterior circumference of the combustor cap barrel flange. 
     
     
         6 . The combustor cap assembly of  claim 1 , wherein each support strut has an airfoil shape with a rounded leading edge and a tapered trailing edge. 
     
     
         7 . The combustor cap assembly of  claim 1 , wherein a leading edge of each support strut is angled with respect to the outer circumference of the combustor cap and the inner circumference of the combustor cap barrel flange such that the portion of the leading edge that is coupled to the combustor cap is located further forward than the portion of the leading edge that is coupled to the combustor cap barrel flange. 
     
     
         8 . The combustor cap assembly of  claim 7 , wherein each support strut has an airfoil shape with a rounded leading edge and a tapered trailing edge. 
     
     
         9 . A support strut configured to mount a combustor cap to a combustor cap barrel flange of a combustor of a turbine engine, comprising:
 a main body having an inner end that is configured to be attached to the outer circumference of a combustor cap and an outer end that is configured to be attached to an inner circumference of a combustor cap barrel flange; and   an interior passageway that extends through the main body between an entrance aperture and an exit aperture.   
     
     
         10 . The support strut of  claim 9 , wherein the entrance aperture is located on a sidewall of the main body and the exit aperture is located on the outer end of the support strut. 
     
     
         11 . The support strut of  claim 10 , wherein the entrance aperture is located on a leading edge of the main body. 
     
     
         12 . The support strut of  claim 9 , wherein the main body has an airfoil shape with a rounded leading edge and a tapered trailing edge. 
     
     
         13 . The support strut of  claim 9 , wherein the inner and outer ends are substantially parallel to one another, wherein a leading edge of the main body forms an oblique angle with the inner end, and wherein a trailing edge of the main body forms an acute angle with the inner end. 
     
     
         14 . The support strut of  claim 13 , wherein the main body has an airfoil shape with a rounded leading edge and a tapered trailing edge. 
     
     
         15 . The support strut of  claim 14 , wherein the entrance aperture is located on the leading edge of the main body and the exit aperture is located on the outer end of the main body.