Patent ID: 9682450
Date: 2017-06-20
CPC Classifications: B23P,F01D,F02C,F05D,Y02T,Y10T

Claim:
1. A gas turbine engine fan section comprising: a fan hub configured to rotate about an axis; a nose cone including a spinner operatively mounted to the fan hub, the spinner supporting a first fastening element, and the nose cone including a cover arranged over the first fastening element, and the nose cone includes circumferentially arranged access holes in an aerodynamic exterior surface of the nose cone, and at least one of the access holes arranged opposite of and aligned with a second fastening element; the second fastening element cooperating with the first fastening element to secure the spinner relative to the fan hub, the first and second fastening elements oriented transversely to the axis, multiple second fastening elements accessible through different access holes; and wherein the spinner and cover provide an aerodynamic exterior surface of the nose cone, and the first and second fastening elements do not provide a portion of the aerodynamic exterior surface.