Strut for an aircraft engine

Abstract

A strut for a gas turbine engine includes a body defining a first side and an opposite second side. The first side is spaced from the second side along the circumferential direction of the gas turbine engine. Additionally, the body includes an inner section, a middle section, and an outer section. Each of the inner, middle, and outer sections are arranged in series order along a span of the strut and define a thickness between the first and second sides of the strut. The thickness of the middle section is greater than the thicknesses of the inner section and of the outer section to increase the strut's resistance to buckling in response to forces exerted thereon.

What is claimed is: 
     
         1 . A strut for a gas turbine engine defining a circumferential direction, the strut defining a span and comprising:
 a body defining a first side and an opposite second side, the first side spaced from the second side along the circumferential direction, the body comprising an inner section, a middle section, and an outer section arranged in series order along the span of the strut, the inner section, middle section, and outer section each defining a thickness between the first and second sides, the thickness of the middle section being greater than the thicknesses of the inner section and the outer section.   
     
     
         2 . The strut of  claim 1 , wherein the strut is formed of a composite material. 
     
     
         3 . The strut of  claim 1 , wherein the thickness of middle section is at least about ten percent (10%) greater than the thicknesses of the inner section and of the outer section. 
     
     
         4 . The strut of  claim 1 , wherein the thickness of middle section is at least about fifteen percent (15%) greater than the thicknesses of the inner section and of the middle section. 
     
     
         5 . The strut of  claim 1 , wherein the inner section comprises an inner thirty percent of the span of the strut, wherein the middle section comprises a middle forty percent of the span of the strut, and wherein the outer section comprises the outer thirty percent of the span of the strut. 
     
     
         6 . The strut of  claim 1 , wherein the thicknesses of the inner section, middle section, and outer section are each measured proximate the aft end of the strut. 
     
     
         7 . The strut of  claim 1 , wherein the body defines an inner end and an outer end, wherein the strut defines a midline extending from the inner end to the outer end through a thickest portion of the body, and wherein the thicknesses of the inner section, middle section, and outer section are measured through the midline. 
     
     
         8 . The strut of  claim 7 , wherein the thickness of the inner section is a minimum thicknesses of the inner section, wherein the thickness of the outer section is a minimum thicknesses of the outer section, and wherein the thickness of the middle section is the maximum thickness of the middle section. 
     
     
         9 . The strut of  claim 1 , wherein the body defines a hollow cavity between the first surface and the second surface extending substantially from the inner end to the outer end. 
     
     
         10 . The strut of  claim 1 , wherein the body defines an inner end and an outer end, wherein the strut further comprises an outer T-shaped mounting flange formed integrally with the body at the outer end of the body. 
     
     
         11 . The strut of  claim 10 , wherein the T-shaped mounting flange comprises oppositely extending projections for mounting the strut, wherein the oppositely extending projections define a thickness, and wherein the thickness of the oppositely extending projections is less than or equal to about half of the thickness of the outer section. 
     
     
         12 . A strut assembly for a gas turbine engine defining a circumferential direction, the strut assembly comprising:
 an inner hub;   an outer structural case; and   a strut extending between the inner hub and the outer structural case, the strut defining a span and a midline extending along the span through a thickest portion of the strut, the strut further defining a first side and an opposite second side, the first side spaced from the second side along the circumferential direction, the strut comprising an inner section, a middle section, and an outer section arranged in series order along the span of the strut, the inner section, middle section, and outer section each defining a thickness between the first and second sides extending through the midline, the thickness of the middle section being greater than the thicknesses of the inner section and the middle section.   
     
     
         13 . The strut assembly of  claim 12 , wherein the body defines an inner end and an outer end, wherein the midline extends from the inner end to the outer end. 
     
     
         14 . The strut assembly of  claim 12  wherein the thickness of the inner section is a minimum thicknesses of the inner section, wherein the thickness of the outer section is a minimum thicknesses of the outer section, and wherein the thickness of the middle section is the maximum thickness of the middle section. 
     
     
         15 . The strut assembly of  claim 12 , wherein the thickness of middle section is at least about 10% greater than the thicknesses of the inner section and of the middle section. 
     
     
         16 . The strut assembly of  claim 12 , wherein the body defines an inner end and an outer end, wherein the body comprises an outer T-shaped mounting flange at the outer end. 
     
     
         17 . The strut assembly of  claim 16 , wherein the T-shaped mounting flange comprises oppositely extending projections for mounting the strut, wherein the oppositely extending projections define a thickness, and wherein the thickness of the oppositely extending projections is about half of the thickness of the outer section. 
     
     
         18 . The strut assembly of  claim 12 , wherein the strut assembly is a forward strut assembly for a fan section of the gas turbine engine. 
     
     
         19 . The strut assembly of  claim 12 , wherein the strut comprises a plurality of struts, wherein the plurality of struts includes between thirteen and twenty-one struts. 
     
     
         20 . The strut assembly of  claim 12 , wherein the strut assembly defines an inner hub radius and an outer structural case radius, and wherein a ratio of the inner hub radius to the outer structural case radius is less than about 1:4.