compressed air is delivered to combustor 16 airflow from combustor 16 drives turbines 18 and 20 before exiting gas turbine engine 10 0015 fig2 is a cross sectional illustration of a portion of gas turbine engine 10 fig3 is a perspective view of a ring support 30 shown in fig2 fig4 is an enlarged cross sectional view of a portion of ring support 30 engine 10 includes a combustor backbone frame 32 that extends circumferentially around combustor 16 to provide structural support to a combustor casing not shown that is coupled thereto and extends circumferentially around combustor 16 engine casing not shown is coupled to backbone frame 32 and also extends circumferentially around engine 10 ring support 30 is coupled to combustor backbone frame 32 ring support 30 is annular and includes an annular upstream radial flange 34 an annular downstream radial flange 36 and a plurality of beams 38 that extend therebetween in the exemplary embodiment upstream and downstream flanges 34 and 36 are substantially circular and are substantially parallel more specifically flange 34 is spaced an axial distance 40 from flange 36 wherein distance 40 defines a width for ring support 30 upstream flange 34 includes an upstream surface 50 a downstream surface 52 and a body 54 that extends therebetween body 54 has a thickness 56 measured between surfaces 50 and 52 and in the exemplary embodiment body 54 is substantially planar flange 34 also has an inner diameter d 1 that is defined by an inner edge 56 of body 54 and an outer diameter d 2 that is defined by an outer edge 58 of body 54 a plurality of openings 62 extend through flange 34 between surfaces 50 and 52 downstream flange 36 includes an upstream surface 70 a downstream surface 72 and a.