Integrated inner case heat shield

1. A mid-turbine frame for a gas turbine engine, comprising:

a first frame case;

a flange coupling a conduit to the first frame case;

a heat shield adjacent to the flange and spaced apart from adjacent spokes, the heat shield defining an opening for receiving the conduit; and

wherein the heat shield defines a cooling cavity, and the cooling cavity has an outlet defined between an outer perimeter of the conduit and an inner perimeter of the opening such that the opening is in direct fluid communication with the cooling cavity;

wherein the heat shield includes a first portion and a second portion, the first portion extends in a circumferential direction, the second portion extends in a radial direction and abuts the first frame case;

wherein a perimeter of the heat shield mates with a perimeter of the flange; and

wherein the cooling cavity has an inlet bounded by the first frame case and spaced apart from the conduit, the outlet has a ring shaped geometry, the first portion extends in an axial direction with respect to a longitudinal axis defined by the first frame case, the conduit extends in a radial direction with respect to the longitudinal axis, the first portion defines the outlet, the second portion defines the perimeter of the heat shield and extends in the radial direction with respect to the longitudinal axis, and the perimeter of the heat shield has a generally triangular geometry that defines the inlet.

2. The mid-turbine frame as recited in claim 1 , wherein the flange is at least partially received in the first frame case.

3. The mid-turbine frame as recited in claim 1 , comprising a second frame case coaxial with the first frame case, and wherein the conduit extends through an airfoil between the first and second frame cases.

4. The mid-turbine frame as recited in claim 3 , wherein the first and second frame cases bound a core flow path, and the airfoil is positioned in the core flow path.

5. The mid-turbine frame as recited in claim 3 , wherein the conduit includes a distal portion extending through the airfoil and a proximal portion coupled to the flange, the distal portion surrounded by an insulated sheath terminating at the proximal portion, and the heat shield extends a distance along the proximal portion.

6. The mid-turbine frame as recited in claim 3 , wherein the conduit is configured to communicate fluid with a bearing compartment.

7. The mid-turbine frame as recited in claim 1 , comprising:

a second frame case;

a plurality of spokes connecting the first and second frame cases; and

wherein the heat shield is spaced in a circumferential direction from each of the plurality of spokes.

8. A gas turbine engine, comprising:

a mid-turbine frame axially between a first turbine and a second turbine, the mid-turbine frame comprising:

a plurality of airfoils radially between an inner frame case and an outer frame case;

a plurality of flanges coupled to the inner frame case;

a plurality of conduits between the inner and outer frame cases, the plurality of conduits coupled to the plurality of flanges; and

a plurality of localized heat shields each corresponding to one of the plurality of flanges, each of the plurality of localized heat shields being spaced apart from each other;

wherein each of the plurality of localized heat shields includes a first portion and a second portion, the first portion extends in a circumferential direction, the second portion extends in a radial direction and abuts the inner frame case;

wherein a perimeter of each of the plurality of localized heat shields mates with a perimeter of a respective one of the plurality of flanges; and

wherein each heat shield of the plurality of heat shields defines a cavity between the inner frame case and one of the plurality of flanges, the cooling cavity has an inlet bounded by the inner frame case and spaced apart from a respective one of the plurality of conduits, the outlet has a ring shaped geometry, the first portion extends in an axial direction with respect to a longitudinal axis defined by the outer frame case, the conduit extends in a radial direction with respect to the longitudinal axis, the first portion defines the outlet, the second portion defines the perimeter of the respective one of the plurality of localized heat shields and extends in the radial direction with respect to the longitudinal axis, and the perimeter of the respective one of the plurality of localized heat shields has a generally triangular geometry that defines the inlet.

9. The gas turbine engine as recited in claim 8 , wherein at least one of the plurality of conduits is configured to communicate cooling airflow with a bearing compartment.

10. The gas turbine engine as recited in claim 8 , wherein the plurality of conduits include a first conduit and a second conduit, the first conduit being an oil supply line and the second conduit being an oil scavenge line, and each of the first and second conduits is coupled to a bearing compartment.

11. The gas turbine engine as recited in claim 8 , wherein opposed walls of the inner and outer frame cases bound a core flow path, and the plurality of airfoils are located in the core flow path.

12. The gas turbine engine as recited in claim 11 , wherein the plurality of localized heat shields are arranged between the plurality of airfoils and surfaces of the plurality of flanges.

13. The gas turbine engine as recited in claim 8 , wherein each heat shield of the plurality of heat shields is spaced circumferentially about the inner frame case.

14. The gas turbine engine as recited in claim 13 , wherein each of the plurality of localized heat shields defines an opening for receiving a respective one of the plurality of conduits, and the outlet is defined between an outer perimeter of a respective one of the plurality of conduits and an inner perimeter of the opening of a respective one of the plurality of localized heat shields such that the opening is in direct fluid communication with the cooling cavity.

15. A method of cooling a portion of a gas turbine engine, comprising:

directing cooling airflow through an inlet between a turbine case and a heat shield;

directing cooling airflow from the inlet to a cavity;

directing airflow from the cavity through an outlet between a conduit and the heat shield; and

wherein the cavity is defined between the heat shield and a flange, and the cavity is defined between the heat shield and the conduit coupled to the flange such that the cavity is in direct fluid communication with the outlet;

wherein the heat shield includes a first portion and a second portion, the first portion extends in a circumferential direction, the second portion extends in a radial direction and abuts the first frame case;

wherein a perimeter of the heat shield mates with a perimeter of the flange; and

wherein the inlet is bounded by the turbine case and is spaced apart from the conduit, the outlet has a ring shaped geometry, the first portion extends in an axial direction with respect to a longitudinal axis defined by the turbine case, the conduit extends in a radial direction with respect to the longitudinal axis, the first portion defines the outlet, the second portion defines the perimeter of the heat shield and extends in a radial direction with respect to the longitudinal axis, and the perimeter of the heat shield has a generally triangular geometry that defines the inlet.

16. The method as recited in claim 15 , wherein the heat shield is arranged between an airfoil receiving the conduit and surfaces of the flange.

17. The method as recited in claim 16 , comprising directing airflow from the outlet into an airfoil cavity defined by the airfoil, the airfoil cavity and the cooling cavity being separated by the heat shield, and the ring shaped geometry follows a perimeter of the conduit.

18. The method as recited in claim 15 , wherein the conduit is coupled to a bearing compartment.