Gas turbine engine turbine diaphragm with angled holes

摘要

A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).

主权项

1. A gas turbine engine turbine diaphragm, comprising:
an inner cylindrical portion; a mounting portion located radially outward from the inner cylindrical portion; and a disk portion extending radially between the inner cylindrical portion and the mounting portion, the disk portion having
a plurality of angled holes, each angled hole following a vector which is angled in at least one plane with a component of the vector being located on a plane perpendicular to a radial extending from an axis of the diaphragm, the component of the vector being angled relative to an axial direction of the diaphragm; anda plurality of first stress relief regions, each first stress relief region being contiguous to one of the plurality of angled holes with each first stress relief region having a curved and an elongated profile, the first stress relief region being wider than a diameter of the one of the plurality of angled holes.