TURBINE BLADE PIN SEAL

摘要

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.

主权项

1. A pin seal for a gas turbine engine with a turbine disk and a plurality of turbine blades, the pin seal comprising:
a body having a cylindrical shape; a first end; and a second end, opposite and distal to the first end; wherein the pin seal is configured to be installed between two adjacent turbine blades within a pressure side seal slot that extends into a pressure side slash face of a first turbine blade and a suction side seal slot that extends into a suction side slash face of a second turbine blade, and the length of the pin seal is configured such that the pin seal extends forward of an airfoil leading edge of each adjacent turbine blade at least by 0.020 inches when the pin seal is in contact with either an aft pressure side surface located at an end of the pressure side seal slot distal to the leading edge of each airfoil or an aft suction side surface located at an end of the suction side seal slot distal to the leading edge of each airfoil, and wherein the pin seal is angled from three to ten degrees in a radial direction relative to an axis of the gas turbine engine during operation of the gas turbine engine.