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 extending from the lower surface, the shank having a base defining a base plane;
• a leading edge inlet passage located within the shank, the leading-edge inlet passage having:
• a first cross-sectional area at a first plane, the first plane radially spaced 0.0167 meters from the base plane;
• a second cross-sectional area at a second plane, the second plane radially spaced 0.0182 meters from the base plane, a first ratio of the second cross-sectional area and the first cross-sectional area defining a second normalized area (Â2) in a range of 0.996 to 1.139;
• a third cross-sectional area at a third plane, the third plane radially spaced 0.0212 meters from the base plane, a second ratio of the third cross-sectional area and the first cross-sectional area defining a third normalized area (Â3) in a range of 1.485 to 1.620;
• a fourth cross-sectional area at a fourth plane, the fourth plane radially spaced 0.0226 meters from the base plane, a third ratio of the fourth cross-sectional area and the first cross-sectional area defining a fourth normalized area (Â4) in a range of 1.743 to 1.861;
• a fifth cross-sectional area at a fifth plane, the fifth plane radially spaced 0.0277 meters from the base plane, a fourth ratio of the fifth cross-sectional area and the first cross-sectional area defining a fifth normalized area (Â5) in a range of 1.155 to 1.262;
• a sixth cross-sectional area at a sixth plane, the sixth plane radially spaced 0.0295 meters from the base plane, a seventh ratio of the sixth cross-sectional area and the first cross-sectional area defining a sixth normalized area (Â6) in a range of 1.039 to 1.179;
• and
• a seventh cross-sectional area at a seventh plane, the seventh plane radially spaced 0.0341 meters from the base plane, a sixth ratio of the seventh cross-sectional area and the first cross-sectional area defining a seventh normalized area (Â7) in a range of 0.890 to 1.078;
• and
• a plurality of cooling conduits located within the airfoil, the plurality of cooling conduits including a group of suction side cooling conduits proximate to the suction side, the group of suction side cooling conduits having a first sum of areas at an eighth plane radially spaced 0.0400 meters from the base plane, the group of suction side cooling conduits having a second sum of areas at an ninth plane radially spaced 0.0476 meters from the base plane, an average of the first sum and the second sum defining a suction side cross-sectional area (SSA), wherein the suction side cross-sectional area (SSA) is from 0.000005 m2 to 0.00000945 m2, and wherein,
• 1211.444
• ≤
• 4
• *
• (
• Â
• 2
• +
• Â
• 6
• Â
• 7
• )
• *
• (
• Â
• 3
• Â
• 5
• )
• Â
• 4
• *
• (
• 0
• .
• 0
• ⁢
• 05
• ⁢
• m
• 2
• SSA
• ⁢
• (
• m
• 2
• )
• )
• *
• (
• SRSR
• ⁢
• (
• m
• )
• 1
• ⁢
• m
• )
• ≤
• 449
• ⁢
• 0
• ⁢
• .406
• .