Cooling passages for a mid-turbine frame
A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. At least one spoke includes a cooling airflow passage that extends through the inner frame case and the bearing support member.
1. A mid-turbine frame for a gas turbine engine comprising:
an inner frame case;
a bearing support member located adjacent the inner frame case; and
at least one spoke attached to the inner frame case, wherein the at least one spoke includes an elongated cylindrical portion extending in a radial direction forming a cooling airflow passage extending through the inner frame case and the cooling airflow passage includes an axially extending branch;
a fitting connecting the axially extending branch of the cooling airflow passage to the inner frame case, wherein the fitting includes a transfer tube connecting the at least one spoke to a cup boss, the transfer tube is fixed relative to the at least one spoke and moveable relative to the cup boss.
2. The mid-turbine frame of claim 1 , wherein the cooling airflow passage includes a branch extending in a radial direction.
3. The mid-turbine frame of claim 2 , wherein the branch extending in the radial direction is in fluid communication with a bearing support cavity.
4. The mid-turbine frame of claim 3 , further comprising a swirler tube connected to the fitting for directing cooling airflow in a direction of rotation of a low pressure rotor.
5. The mid-turbine frame of claim 3 , wherein the cooling airflow passage includes a circular cross section in a first portion of the cup boss and a race track cross section in a second portion of the cup boss.
6. The mid-turbine frame of claim 1 , wherein the inner frame case and the bearing support member each include a race track shaped opening aligned with the cooling airflow passage.
7. 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 inner frame case;
a bearing support member located adjacent the inner frame case;
at least one spoke attached to the inner frame case, wherein the at least one spoke includes a cooling airflow passage extending through the inner frame case and the bearing support member wherein the at least one spoke includes an elongated cylindrical portion extending in a radial direction forming the cooling airflow passage having a branch extending in an axial direction; and
a fitting connecting the branch extending in the axial direction to the inner frame case, wherein the fitting includes a transfer tube connecting the at least one spoke to a cup boss, the transfer tube is fixed relative to the at least one spoke and moveable relative to the cup boss.
8. The gas turbine engine of claim 7 , wherein the cooling airflow passage includes a branch extending in a radial direction.
9. The gas turbine engine of claim 8 , wherein the branch extending in the radial direction is in fluid communication with a bearing support cavity.
10. The gas turbine engine of claim 7 , further comprising a swirler tube connected to the fitting for directing cooling airflow in a direction of rotation of a low pressure rotor.
11. The gas turbine engine of claim 7 , wherein the cooling airflow passage includes a circular cross section in a first portion of the cup boss and a race track cross section in a second portion of the cup boss.
12. The gas turbine engine of claim 7 , wherein the inner frame case and the bearing support member each include a race track shaped opening aligned with the cooling airflow passage.