Integrated inner case heat shield

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.

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.