Turbine engine with a blade assembly having a set of cooling conduits

A blade assembly for a gas turbine engine, the blade assembly comprising:

• a platform having an upper surface and a lower surface, the platform having a stator rotor seal with an upper edge having a radius of curvature defined as a stator rotor seal radius (SRSR), wherein the stator rotor seal radius (SRSR) is 0.224 meters to 0.239 meters;
• an airfoil extending from the upper surface of the platform, the airfoil having an exterior surface, the exterior surface defining a pressure side and a suction side, the airfoil including a leading-edge and a trailing-edge;
• a shank coupled to the lower surface, the shank having a base defining a base plane;
• and
• a middle inlet passage located within the shank, the middle inlet passage having:
• a first cooling conduit portion at a first plane radially spaced 0.0167 meters from the base plane, the first cooling conduit portion having a first cross-sectional area, the first cooling conduit portion defining a first bounding circle, the first cooling conduit portion having:
• a first point at a first 12:30 o'clock position on the first bounding circle;
• and
• a second point at a first 1:30 o'clock position on the first bounding circle, the first point and the second point defining a first line;
• a second cooling conduit portion at a second plane radially spaced 0.0197 meters from the base plane, the second cooling conduit portion having a second cross-sectional area;
• a third cooling conduit portion at a third plane radially spaced 0.0215 meters from the base plane, the third cooling conduit portion having a third cross-sectional area;
• a fourth cooling conduit portion at a fourth plane radially spaced 0.0234 meters from the base plane, the fourth cooling conduit portion having a fourth cross-sectional area;
• a fifth cooling conduit portion at a fifth plane radially spaced 0.0245 meters from the base plane, the fifth cooling conduit portion having a fifth cross-sectional area, the fifth cooling conduit portion defining a second bounding circle, the second cooling conduit portion having:
• a third point at a second 12:30 o'clock position on the second bounding circle;
• and
• a fourth point at a second 1:30 o'clock position on the second bounding circle, the third point and the fourth point defining a second line;
• wherein the middle inlet passage defines a maximum normalized cooling conduit portion area (Amax) ranging between 1.30 and 2.10, Amax defined by:
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• wherein the first line and the second line define a degree of change of the cooling conduit portions along the suction side (DCCPASS) ranging between 21.0 and 33.0 degrees (°);
• and
• a plurality of cooling conduits located within the airfoil, the plurality of cooling conduits including a first quantity (N1) of cooling conduits fed by the middle inlet passage, wherein the first quantity is 2, wherein the plurality of cooling conduits define a second quantity (N2) of cooling conduit portions spanning between the suction side and the pressure side, wherein the second quantity is 3, and wherein:
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