Laterally biased system for mounting auxiliary components to gas turbine engines
A mounting assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a first flange configured for attaching the mounting assembly to the engine case; a second flange configured for attaching the mounting assembly to the auxiliary component; and a mechanical fuse disposed between the first flange and the second flange and configured to shear during an overload event.
1. A mounting assembly for mounting an auxiliary component to an engine case of a gas turbine engine, the engine case extending along an axial direction with respect to a central rotational axis of the gas turbine engine and extending along a lateral direction with respect to the central rotational axis of the gas turbine engine, comprising:
a first flange configured for attaching the mounting assembly to the engine case;
a second flange configured for attaching the mounting assembly to the auxiliary component; and
a mechanical fuse disposed between the first flange and the second flange and configured to shear during an overload event, the mechanical fuse includes:
a center portion connected to the second flange and extending away from the second flange and toward the first flange, the center portion defines a rectangular block bounded by a first lateral side and a second lateral side;
a first fuse member spaced a first lateral distance from the first lateral side; and
a second fuse member spaced a second lateral distance from the second lateral side.
2. The mounting assembly of claim 1 , wherein the mechanical fuse is configured to shear in reaction to a load applied in the lateral direction.
3. The mounting assembly of claim 1 , wherein the mechanical fuse includes a first wall member connected to the first flange and extending away from the first flange and toward the second flange, the first wall member configured to abut the first fuse member.
4. The mounting assembly of claim 3 , wherein the mechanical fuse includes a second wall member connected to the first flange and extending away from the first flange and toward the second flange, the second wall member configured to abut the second fuse member.
5. The mounting assembly of claim 4 , wherein the first fuse member includes a first fuse section, the first fuse section being formed by a first lateral gap positioned proximate a first base portion that is connected to the first fuse member.
6. The mounting assembly of claim 5 , wherein the second fuse member includes a second fuse section, the second fuse section being formed by a second lateral gap positioned proximate a second base portion that is connected to the second fuse member.
7. The mounting assembly of claim 6 , wherein a first boss is connected to the first flange and configured to be received in a first recess portion of a plate attached to the engine case.
8. The mounting assembly of claim 7 , wherein a second boss is connected to the second flange and configured to be received in a second recess portion extending into the auxiliary component.
9. A gas turbine engine, comprising:
an engine case, the engine case including a plate for mounting a gearbox; and
a mounting assembly for mounting the gearbox to the engine case, the engine case extending along an axial direction with respect to a central rotational axis of the gas turbine engine, the mounting assembly including
a first flange configured for attaching the mounting assembly to the engine case,
a second flange configured for attaching the mounting assembly to the gearbox, and
a mechanical fuse disposed between the first flange and the second flange and configured to shear during an overload event, the mechanical fuse includes:
a center portion connected to the second flange and extending away from the second flange and toward the first flange, the center portion defines a rectangular block bounded by a first lateral side and a second lateral side;
a first fuse member spaced a first lateral distance from the first lateral side; and
a second fuse member spaced a second lateral distance from the second lateral side.
10. The gas turbine engine of claim 9 , wherein the mechanical fuse is configured to shear in reaction to a load applied in a lateral direction, the lateral direction being a circumferential direction with respect to the axial direction.
11. The gas turbine engine of claim 9 , wherein the mechanical fuse includes a first wall member connected to the first flange and extending away from the first flange and toward the second flange, the first wall member configured to abut the first fuse member, and a second wall member connected to the first flange and extending away from the first flange and toward the second flange, the second wall member configured to abut the second fuse member.
12. The gas turbine engine of claim 11 , wherein the first fuse member includes a first fuse section, the first fuse section being formed by a first lateral gap positioned proximate a first base portion that is connected to the first fuse member, and a second fuse section, the second fuse section being formed by a second lateral gap positioned proximate a second base portion that is connected to the second fuse member.
13. The gas turbine engine of claim 12 , wherein a first boss is connected to the first flange and configured to be received in a first recess portion of the plate attached to the engine case, and a second boss is connected to the second flange and configured to be received in a second recess portion extending into the gearbox.