Turbine blade with a pin seal slot

Abstract

A gas turbine engine turbine disk assembly includes a turbine disk, turbine blades, and pin seals. Each turbine blade includes a platform with a pressure side seal slot extending into a pressure side of the platform and a suction side seal slot extending into a suction side of the platform. The pressure side seal slot and the suction side seal slot are each angled between three and ten degrees in the radial direction relative to the axis of the turbine disk. The pin seal includes a cylindrical shape and is located within a seal slot formed from the pressure side seal slot and the suction side seal slot of adjacent turbine blades.

What is claimed is: 
     
         1 . A turbine blade for a gas turbine engine having a turbine disk with an axis, the turbine blade comprising:
 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 the pressure side platform from the pressure side slash face, the pressure side seal slot being 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 a forward portion of the pressure side seal slot being radially closer to the reference axis than an aft portion of the pressure side seal 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 the suction side platform from the suction side slash face, the suction side seal slot being angled between three and ten degrees in the radial direction relative to the reference axis with a forward portion of the suction side seal slot being radially closer to the reference axis than an aft portion of the suction side seal slot. 
 
   
     
     
         2 . The turbine blade of  claim 1 , wherein the pressure side seal slot and the suction side seal slot are angled from four to six degrees in the radial direction relative to the reference axis. 
     
     
         3 . The turbine blade of  claim 1 , wherein the pressure side seal slot and the suction side seal slot are angled within a predetermined tolerance of five degrees in the radial direction relative to the reference axis. 
     
     
         4 . The turbine blade of  claim 1 , wherein the pressure side seal slot includes a pressure side sealing surface, the pressure side sealing surface being angled between three and ten degrees in a radial direction relative to the reference axis, the pressure side sealing surface being angled with a forward portion of the pressure side sealing surface being radially closer to the reference axis than an aft portion of the pressure side sealing surface, and wherein the suction side seal slot includes a suction side sealing surface, the suction side sealing surface being angled between three and ten degrees in the radial direction relative to the reference axis with a forward portion of the suction side sealing surface being radially closer to the reference axis than an aft portion of the suction side sealing surface. 
     
     
         5 . The turbine blade of  claim 4 , wherein the pressure side sealing surface and the suction side sealing surface are angled from four to six degrees in the radial direction relative to the reference axis. 
     
     
         6 . The turbine blade of  claim 4 , wherein the pressure side sealing surface and the suction side sealing surface are angled within a predetermined tolerance of five degrees in the radial direction relative to the reference axis. 
     
     
         7 . The turbine blade of  claim 4 , wherein the pressure side sealing surface extends from the pressure side slash face toward the blade root at an angle from sixty to seventy degrees relative to a reference plane extending through the blade root, the reference plane being a center plane of the blade root, and the suction side sealing surface extends from the suction side slash face toward the blade root at an angle from forty to fifty degrees relative to the reference plane. 
     
     
         8 . A turbine disk assembly including two turbine blades of  claim 7 , wherein the pressure side slash face of a first turbine blade is parallel and adjacent to the suction side slash face of a second turbine blade, and the pressure side sealing surface of the first turbine blade and the suction side sealing surface of the second turbine blade form an angle from ninety-five to one-hundred fifteen degrees therebetween. 
     
     
         9 . A gas turbine engine including the turbine blade of  claim 1 . 
     
     
         10 . A turbine blade for a gas turbine engine having a turbine disk with an axis, the turbine blade comprising:
 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 suction side slash face, 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. 
 
 
   
     
     
         11 . The turbine blade of  claim 10 , wherein the pressure side seal slot includes a pressure side sealing surface spanning the length of the pressure side seal slot, the pressure side sealing surface extending from the pressure side slash face toward the blade root in a direction opposite the direction that the pressure side platform extends and in the same direction that blade root extends, and the suction side seal slot includes a suction side sealing surface spanning the length of the suction side seal slot, the suction side sealing surface extending from the suction side slash face toward the blade root in a direction opposite the direction that the suction side platform extends and in the same direction that blade root extends. 
     
     
         12 . The turbine blade of  claim 11 , further comprising wherein the pressure side sealing surface is angled from sixty to seventy degrees relative to a reference plane extending through the blade root, the reference plane being a plane of symmetry of the blade root, and the suction side sealing surface is angled from forty to fifty degrees relative to the reference plane. 
     
     
         13 . The turbine blade of  claim 12 , wherein the pressure side sealing surface is angled from sixty-four to sixty-six degrees relative to the reference plane and the suction side sealing surface is angled from forty-four to forty-six degrees relative to the reference plane. 
     
     
         14 . The turbine blade of  claim 11 , further comprising:
 a forward pressure side damper buttress extending from the pressure side platform adjacent the forward end and extending down adjacent the blade root, the forward pressure side damper buttress including a forward pressure damper surface;   an aft pressure side damper buttress extending from the pressure side platform adjacent the aft end and extending down adjacent the blade root, the aft pressure side damper buttress including an aft pressure damper surface, the aft pressure damper surface faces towards the forward pressure damper surface and the forward pressure damper surface faces towards the aft pressure damper surface;   a pressure side underplatform surface extending between the forward pressure damper surface and the aft pressure damper surface along the pressure side platform, wherein a portion of pressure side sealing surface extending between the forward pressure side slot and the aft pressure side slot extends from the pressure side slash face to the pressure side underplatform surface;   a forward suction side damper buttress extending from the suction side platform adjacent the forward end and extending down adjacent the blade root, the forward suction side damper buttress including a forward suction damper surface;   an aft suction side damper buttress extending from the suction side platform adjacent the aft end and extending down adjacent the blade root, the aft suction side damper buttress including an aft suction damper surface, the aft suction damper surface faces towards the forward suction damper surface and the forward suction damper surface faces towards the aft suction damper surface; and   a suction side underplatform surface extending between the forward suction damper surface and the aft suction damper surface along the suction side platform, wherein a portion of suction side sealing surface extending between the forward suction side slot and the aft suction side slot extends from the suction side slash face to the suction side underplatform surface.   
     
     
         15 . A gas turbine engine including the turbine blade of  claim 10 . 
     
     
         16 . 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; and 
   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, 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 the 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 including 
  a forward pressure side slot including a concave shape, the forward pressure side slot being the axially forward portion of the pressure side seal slot, 
  an aft pressure side slot including a concave shape, the aft pressure side slot being the axially aft portion of the pressure side seal slot, and 
  a pressure side sealing surface extending from the pressure side slash face radially inward and circumferentially toward the blade root, the pressure side sealing surface being angled between three and ten degrees in the radial direction relative to the axis with a forward portion of the pressure side sealing surface being radially closer to the axis than an aft portion of the pressure side sealing surface, 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 including 
  a forward suction side slot including a concave shape, the forward suction side slot being the axially forward portion of the suction side seal slot, 
  an aft suction side slot including a concave shape, the aft suction side slot being the axially aft portion of the suction side seal slot, and 
  a suction side sealing surface extending from the suction side slash face radially inward and circumferentially toward the blade root and angled from ninety-five to one-hundred fifteen degrees relative to the pressure side sealing surface, and the suction side sealing surface being angled between three and ten degrees in the radial direction relative to the axis with a forward portion of the suction side sealing surface being radially closer to the axis than an aft portion of the suction side sealing surface. 
 
 
   
     
     
         17 . The turbine disk assembly of  claim 16 , wherein the pressure side seal slot and the suction side seal slot are angled between three and ten degrees in the radial direction relative to the axis with the forward pressure side slot and the forward suction side slot being radially closer to the axis than the aft pressure side slot and the aft suction side slot. 
     
     
         18 . The turbine disk assembly of  claim 16 , wherein the suction side sealing surface is angled within a predetermined tolerance of one-hundred five degrees relative to the pressure side sealing surface. 
     
     
         19 . The turbine disk assembly of  claim 16 , wherein the pressure side sealing surface and the suction side sealing surface are angled within a predetermined tolerance of five degrees in the radial direction relative to the axis. 
     
     
         20 . A gas turbine engine including the turbine disk assembly of  claim 16 .