Retaining assembly for a gas turbine engine
A retaining assembly may comprise a bracket assembly having a first end and a second end. The first end may be configured to mount to a clamping band. The retaining assembly may further comprise a retention component. The retention component may have a clevis coupled to the second end. The retaining assembly may be coupled to an otherwise loose external component on a gas turbine engine. The retaining assembly may keep the otherwise loose external component fixed to the gas turbine engine during maintenance operations and prevent the otherwise loose external component from being lost or misplaced.
1. A clamp assembly, comprising:
a clamping band; and
a retaining assembly, comprising:
a bracket assembly having a first end coupled to the clamping band and a second end; and
a retention component comprising at least one of a spring loaded clip or a spring loaded clamp, the retention component having a clevis coupled to the second end of the bracket assembly, wherein the bracket assembly comprises a first L-bracket having a first hinge aperture and a second L-bracket having a second hinge aperture.
2. The clamp assembly of claim 1 , wherein the clevis and the second end define a fulcrum, the clamping band being able to rotate via the bracket assembly about the fulcrum.
3. The clamp assembly of claim 1 , wherein the retention component comprises at least one of a worm gear or a fastener configured to either loosen or tighten the retention component.
4. The clamp assembly of claim 1 , wherein a first clamping arm of the clamping band is coupled to the first L-bracket and configured to pivot about a first hinge and a second clamping arm of the clamping band is coupled to the second L-bracket and configured to pivot about a second hinge.
5. A gas turbine engine, comprising:
a first tube assembly comprising:
a tube having a straight portion having an outer surface;
a clamp assembly comprising a sleeve having a semi-annular portion, a clevis, and a bracket assembly having a first end and a second end, the sleeve being coupled at the semi-annular portion to the outer surface of the straight portion, the bracket assembly being coupled to the sleeve at an intersection of the second end and the clevis.
6. The gas turbine engine of claim 5 , wherein the intersection defines a fulcrum about which the first end of the bracket assembly is configured to rotate.
7. The gas turbine engine claim 5 , wherein the clamp assembly further comprises a clamping band coupled to the first end of the bracket assembly.
8. The gas turbine engine of claim 5 , wherein the semi-annular portion of the sleeve is fixedly attached via brazing to the outer surface of the straight portion of the first tube assembly.
9. The gas turbine engine of claim 7 , wherein the bracket assembly comprises a first L-bracket having a first hinge aperture and a second L-bracket having a second hinge aperture.
10. The gas turbine engine of claim 9 , wherein a first clamping arm of the clamping band is coupled to the first L-bracket and configured to pivot about a first hinge and a second clamping arm of the clamping band is coupled to the second L-bracket and configured to pivot about a second hinge.
11. The gas turbine engine of claim 7 , further comprising a second tube assembly coupled to the first tube assembly by the clamping band.
12. A clamp assembly, comprising:
a clamping band; and
a retaining assembly, comprising:
a bracket assembly having a first end coupled to the clamping band and a second end; and
a retention component comprising at least one of a chain or a band/strap, the retention component having a clevis coupled to the second end of the bracket assembly, wherein the bracket assembly comprises a first L-bracket having a first hinge aperture and a second L-bracket having a second hinge aperture.