Compliant intermediate component of a gas turbine engine

摘要

One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.

主权项

1. An apparatus comprising:
a first gas turbine engine component structured for use in a gas turbine engine and having a first mating portion; a second gas turbine engine component having a second mating portion formed to receive within it the first mating portion of the first component to interlockingly secure the first component for use during operation of the gas turbine engine; and a load bearing intermediate component positioned between the first mating portion of the first component and the second mating portion of the second component, the load bearing intermediate component including: a main body having a portion configured to bear a loading imparted by contact between the first mating portion and the second mating portion, the main body captured on one of the first mating portion and the second mating portion through a plurality of finger portions extending from the main body, wherein the plurality of finger portions each contact the second mating portion of the second gas turbine engine component at a different location and the plurality of finger portions includes a first finger portion that contacts the second component at a first location, a second finger portion that contacts the second component at a second location spaced from the first location in a circumferential direction, and a third finger portion that contacts the second component at a third location spaced discreetly from the first location in both the circumferential direction and an axial direction.