Patent ID: 6364606
Filing Date: 2002-04-02
Classification: F01D,F05B,F05D

Abstract:
An apparatus for use in a gas turbine engine, comprising:a hanger having a ring shaped portion substantially centered around an axis, the ring shaped portion of the hanger including a first plurality of passages, the first plurality of passages extending substantially radially with respect to the axis; an inner case having a ring shaped portion substantially centered around the axis, the ring shaped portion of the inner case positioned radially outward from the ring shaped portion of the hanger, the ring shaped portion of the inner case including a plurality of openings, the plurality of openings extending substantially radially with respect to the axis, wherein at least one of the plurality of openings is substantially aligned with at least one of the first plurality of passages; and, a first pin extending between a first end and a second end, a first portion of the first pin and the first end both positioned within said at least one of the plurality of openings and a second portion of the first pin positioned within said at least one of the first plurality of passages to couple the hanger to the inner case.