Aircraft blade lock retainer
The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.
1. An engine fan assembly, comprising:
a spinner having an aft flange and a spacer integral to the spinner; and
a blade lock retainer coupled to the aft flange of the spinner, wherein the spacer is disposed between the aft flange of the spinner and the blade lock retainer, the blade lock retainer comprising:
an annular ring portion,
an outer retainer tab portion, disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extending in an aft direction from the annular ring portion, and
an inner retainer tab portion, disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extending in a forward direction from the annular ring portion, wherein the blade lock retainer is formed from sheet metal;
a plurality of rivet apertures; and
at least one bolt aperture disposed in the annular ring portion and radially aligned with the outer retainer tab portion and the inner retainer tab portion;
at least one bolt, the blade lock retainer installable to a hub by the at least one bolt aperture, the at least one bolt aperture configured to receive the at least one bolt;
at least one rivet, the blade lock retainer coupled to the aft flange of the spinner by at least one rivet aperture from the plurality of rivet apertures, the at least one rivet aperture configured to receive the at least one rivet.
2. The engine fan assembly of claim 1 , wherein the annular ring portion, the outer retainer tab portion, and the inner retainer tab portion comprise a substantially uniform thickness.
3. The engine fan assembly of claim 1 , wherein:
the annular ring portion comprises a first thickness;
the outer retainer tab portion comprises a second thickness;
the inner retainer tab portion comprises a third thickness; and
the first thickness is greater than at least one of the second thickness and the third thickness.
4. The engine fan assembly of claim 1 , wherein the blade lock retainer comprises at least one of a metal and a metal alloy.
5. The engine fan assembly of claim 4 , wherein the metal comprises at least one of titanium and aluminum.
6. The engine fan assembly of claim 4 , wherein the metal alloy comprises a nickel alloy.
7. An aircraft engine fan assembly, comprising:
a spinner having an aft flange and a spacer, the spacer integral to the spinner;
a hub:
a blade lock retainer coupled to the aft flange of the spinner, wherein the spacer is disposed between the aft flange of the spinner and the blade lock retainer, and wherein the blade lock retainer is formed from sheet metal and comprises:
an annular ring portion;
an outer retainer tab portion, disposed on an outer circumference of the annular ring portion, oriented perpendicularly to the annular ring portion, and extending in an aft direction from the annular ring portion;
an inner retainer tab portion, disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented perpendicularly to the annular ring portion, and extending in a forward direction from the annular ring portion;
a plurality of rivet apertures; and
at least one bolt aperture disposed in the annular ring portion and radially aligned with the outer retainer tab portion and the inner retainer tab portion;
at least one bolt, the blade lock retainer coupled to the hub by the at least one bolt aperture, the at least one bolt aperture configured to receive the at least one bolt; and
at least one rivet, the blade lock retainer coupled to the aft flange of the spinner by at least one rivet aperture from the plurality of rivet apertures, the at least one rivet aperture configured to receive the at least one rivet.
8. The aircraft engine fan assembly of claim 7 , wherein the blade lock retainer comprises at least one of a metal and a metal alloy.
9. The aircraft engine fan assembly of claim 8 , wherein the metal comprises at least one of titanium and aluminum.
10. The aircraft engine fan assembly of claim 8 , wherein the metal alloy comprises a nickel alloy.
11. The aircraft engine fan assembly of claim 7 , wherein a first radial length of the spacer is equal to a second radial length of the annular ring portion.
12. The aircraft engine fan assembly of claim 7 , wherein a first radial length of the spacer is less than a second radial length of the annular ring portion.
13. The aircraft engine fan assembly of claim 7 , wherein the spacer comprises titanium.
14. The aircraft engine fan assembly of claim 7 , wherein the spacer comprises aluminum.
15. The aircraft engine fan assembly of claim 7 , wherein the spacer comprises a composite material.