A gas turbine engine comprising a mid-turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame comprising: an outer frame case; an inner frame case; and at least one hollow spoke comprising: a cylindrical portion; a cooling airflow passage extending in a radial direction through the cylindrical portion, wherein the cooling airflow passage includes a first branch extending in a radially inward direction through the inner frame case into a bearing support cavity and a second branch extending in an axially downstream direction into a low-rotor cavity; and a flange attached to the cylindrical portion, the flange including a plurality of fastener openings for securing the hollow spoke to the inner frame case, characterised in that: the hollow spoke comprises a first gusset and a second gusset, which are located on opposite sides of a fastener opening in the flange, the first gusset and the second gusset each extending between the cylindrical portion and the flange, wherein the first gusset and the second gusset each extend to a perimeter of the flange; the branch includes a press-fit opening; the gas turbine engine further comprises a fitting connecting the cooling airflow passage to the inner frame case, wherein the second branch is in fluid communication with the low-rotor cavity through said fitting, the fitting includes a transfer tube connecting the at least one hollow spoke to a cup boss, and the transfer tube is pressed into the opening in the hollow spoke on a first end and engages the cup boss on a second end so that the transfer tube is fixed relative to the at least one hollow spoke and moveable relative to the cup boss; and in that radially upper surfaces (160, 156) of each of the first gusset and the second gusset extend outward to a perimeter of the flange and are spaced upward from the perimeter of the flange, or radially upper surfaces (160, 156) of each of the first gusset and the second gusset extend flush with an upper perimeter edge of the flange. an outer frame case; an inner frame case; and at least one hollow spoke comprising: a cylindrical portion; a cooling airflow passage extending in a radial direction through the cylindrical portion, wherein the cooling airflow passage includes a first branch extending in a radially inward direction through the inner frame case into a bearing support cavity and a second branch extending in an axially downstream direction into a low-rotor cavity; and a flange attached to the cylindrical portion, the flange including a plurality of fastener openings for securing the hollow spoke to the inner frame case, a cylindrical portion; a cooling airflow passage extending in a radial direction through the cylindrical portion, wherein the cooling airflow passage includes a first branch extending in a radially inward direction through the inner frame case into a bearing support cavity and a second branch extending in an axially downstream direction into a low-rotor cavity; and a flange attached to the cylindrical portion, the flange including a plurality of fastener openings for securing the hollow spoke to the inner frame case, the hollow spoke comprises a first gusset and a second gusset, which are located on opposite sides of a fastener opening in the flange, the first gusset and the second gusset each extending between the cylindrical portion and the flange, wherein the first gusset and the second gusset each extend to a perimeter of the flange; the branch includes a press-fit opening; the gas turbine engine further comprises a fitting connecting the cooling airflow passage to the inner frame case, wherein the second branch is in fluid communication with the low-rotor cavity through said fitting, the fitting includes a transfer tube connecting the at least one hollow spoke to a cup boss, and the transfer tube is pressed into the opening in the hollow spoke on a first end and engages the cup boss on a second end so that the transfer tube is fixed relative to the at least one hollow spoke and moveable relative to the cup boss; and in that radially upper surfaces (160, 156) of each of the first gusset and the second gusset extend outward to a perimeter of the flange and are spaced upward from the perimeter of the flange, or radially upper surfaces (160, 156) of each of the first gusset and the second gusset extend flush with an upper perimeter edge of the flange.