A gas turbine engine comprising: a bearing support cavity; and a mid turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame including: an outer frame case; an inner frame case including a plurality of cooling holes; a first plurality of airfoils circumferentially spaced around the inner frame case, each surrounding a tie rod having an inlet passage aligned with the cooling holes and in fluid communication with the bearing support cavity to direct cooling airflow into the bearing support cavity; a second plurality of airfoils each surrounding a service line and aligned with a leakage gap in 2. the inner frame case and in fluid communication with the bearing support cavity to direct cooling airflow from the bearing support cavity into the airfoil through the leakage gap between the inner frame case and the service line; and characterized by a third plurality of hollow airfoils, wherein each of the third plurality of airfoils is circumferentially and axially aligned with one of a plurality of flow balancing holes in the inner frame case and in fluid communication with the bearing support cavity the flow balancing holes being configured to direct cooling airflow from the bearing support cavity radially outward into the hollow airfoil so as to maintain relatively even cooling of the first, second and third plurality of airfoils. a bearing support cavity; and a mid turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame including: an outer frame case; an inner frame case including a plurality of cooling holes; a first plurality of airfoils circumferentially spaced around the inner frame case, each surrounding a tie rod having an inlet passage aligned with the cooling holes and in fluid communication with the bearing support cavity to direct cooling airflow into the bearing support cavity; a second plurality of airfoils each surrounding a service line and aligned with a leakage gap in 2. the inner frame case and in fluid communication with the bearing support cavity to direct cooling airflow from the bearing support cavity into the airfoil through the leakage gap between the inner frame case and the service line; and characterized by a third plurality of hollow airfoils, wherein each of the third plurality of airfoils is circumferentially and axially aligned with one of a plurality of flow balancing holes in the inner frame case and in fluid communication with the bearing support cavity the flow balancing holes being configured to direct cooling airflow from the bearing support cavity radially outward into the hollow airfoil so as to maintain relatively even cooling of the first, second and third plurality of airfoils. an outer frame case; an inner frame case including a plurality of cooling holes; a first plurality of airfoils circumferentially spaced around the inner frame case, each surrounding a tie rod having an inlet passage aligned with the cooling holes and in fluid communication with the bearing support cavity to direct cooling airflow into the bearing support cavity; a second plurality of airfoils each surrounding a service line and aligned with a leakage gap in 2. the inner frame case and in fluid communication with the bearing support cavity to direct cooling airflow from the bearing support cavity into the airfoil through the leakage gap between the inner frame case and the service line; and characterized by a third plurality of hollow airfoils, wherein each of the third plurality of airfoils is circumferentially and axially aligned with one of a plurality of flow balancing holes in the inner frame case and in fluid communication with the bearing support cavity the flow balancing holes being configured to direct cooling airflow from the bearing support cavity radially outward into the hollow airfoil so as to maintain relatively even cooling of the first, second and third plurality of airfoils.