COMBUSTOR MOUNTING STRUCTURES FOR GAS TURBINE ENGINES

Combustor mounting structures (400; 500; 600; 700; 800; 900; 1000; 1100; 1200) for gas turbine engines (300) are described. The combustor mounting structures (400; 500; 600; 700; 800; 900; 1000; 1100; 1200) include a shell portion (326; 402; 502; 602; 702; 802; 902; 1002; 1102; 1202) defining an outer ring arranged at an outer radius relative to a central axis, a combustor connection element (320; 404; 508; 608; 708; 808; 908; 1008; 1108; 1208) defining an inner ring arranged at an inner radius that is less than the outer radius relative to the central axis, and a plurality of struts (328; 406; 506; 606; 706; 806; 906; 1006; 1106; 1206) extending radially between and connecting the shell portion (326; 402; 502; 602; 702; 802; 902; 1002; 1102; 1202) to the combustor connection element (320; 404; 508; 608; 708; 808; 908; 1008; 1108; 1208), wherein one or more flow apertures (410) are defined between the shell portion (326; 402; 502; 602; 702; 802; 902; 1002; 1102; 1202) and the combustor connection element (320; 404; 508; 608; 708; 808; 908; 1008; 1108; 1208) in a radial direction and between adjacent struts of the plurality of struts (328; 406; 506; 606; 706; 806; 906; 1006; 1106; 1206) in a circumferential direction.