Turbine blade pin seal

A turbine blade assembly for a gas turbine engine having a turbine disk with an axis, the turbine blade assembly comprising:

• a turbine blade having
• an airfoil extending in a first direction, the airfoil having
• a leading edge,
• a trailing edge,
• a pressure side spanning between the leading edge and the trailing edge, and
• a suction side spanning between the leading edge and the trailing edge;
• a blade root extending in a second direction, opposite the first direction, and
• a platform located between the airfoil and the blade root, the platform having
• a forward end adjacent the leading edge,
• an aft end adjacent the trailing edge,
• a pressure side platform extending from the pressure side, the pressure side platform including
• a pressure side slash face distal to the pressure side, the pressure side slash face extending from the forward end to the aft end, and
• a pressure side seal slot extending into pressure side platform from pressure side slash face, the pressure side seal slot including
• a forward pressure side slot located adjacent the forward end spanning a forward portion of the pressure side slash face with a concave shape, and
• an aft pressure side slot located adjacent the aft end spanning an aft portion of the pressure side slash face with a concave shape,
• wherein the pressure side seal slot is angled between three and ten degrees in a radial direction relative to a reference axis located below the blade root, opposite the airfoil, the reference axis being coaxial to the axis of the turbine disk when the turbine blade is installed onto the turbine disk, the pressure side seal slot being angled with the forward pressure side slot being radially closer to the reference axis than the aft pressure side slot, and
• a suction side platform extending away from the suction side in a direction opposite the pressure side platform, the suction side platform including
• a suction side slash face distal to the suction side, the suction side slash face extending from the forward end to the aft end, and
• a suction side seal slot extending into suction side platform from the suction side slash face, the suction side seal slot including
• a forward suction side slot located adjacent the forward end spanning a forward portion of the suction side slash face, and
• an aft suction side slot located adjacent the aft end spanning an aft portion of the suction side slash face,
• wherein the suction side seal slot is angled between three and ten degrees in the radial direction relative to the reference axis with the forward suction side slot being radially closer to the reference axis than the aft suction side slot;
• and
• a pin seal affixed to the turbine blade, the pin seal having
• a body including a cylindrical shape,
• a first end, and
• a second, opposite the first end.

A turbine disk assembly of a gas turbine engine, the turbine disk assembly comprising:

• a turbine disk with a cylindrical shape, the turbine disk having
• disk posts, each disk post extending radially outward from the cylindrical shape, with adjacent disk posts forming a turbine disk slot there between;
• a plurality of turbine blades, each blade having
• an airfoil extending radially outward relative to an axis through the cylindrical shape of the turbine disk, the axis including a forward direction and an aft direction, the airfoil including
• a leading edge,
• a trailing edge axially aft of the leading edge relative to the axis,
• a pressure side spanning between the leading edge and the trailing edge, and
• a suction side spanning between the leading edge and the trailing edge,
• a blade root extending radially inward relative to the axis, the blade root including the shape of the turbine disk slots, and
• a platform located between the airfoil and the blade root, the platform including
• a forward end,
• an aft end axially aft of the forward end,
• a pressure side platform extending from the pressure side in a first circumferential direction relative to the axis, the pressure side platform including
• a pressure side slash face distal to the pressure side, the pressure side slash face extending in a radial direction relative to the axis spanning from the forward end to the aft end, and
• a pressure side seal slot extending into pressure side platform from pressure side slash face, the pressure side seal slot being angled between three and ten degrees in the radial direction relative to the axis, and
• a suction side platform extending from the suction side in a first circumferential direction relative to the axis, the suction side platform including
• a suction side slash face distal to the suction side, the suction side slash face extending in the radial direction relative to the axis spanning from the forward end to the aft end, and
• a suction side seal slot extending into suction side platform from suction side slash face, the suction side seal slot being angled between three and ten degrees in the radial direction relative to the axis;
• and
• a plurality of pin seals, each pin seal having
• a body including a cylindrical shape,
• a first end, and
• a second end opposite the first end;
• wherein each pin seal is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades, each pin seal extending axially forward of the leading edge of each adjacent turbine blade.