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US 12,535,034 B1Granted
Joint between aircraft engine components with spring beams
AssigneePratt & Whitney Canada Corp.
InventorMichael Fryer
Life of this patent
Estimating the term…
Abstract
An assembly includes a case, a housing and a component. The case includes an aperture, an exterior side and an interior side. The aperture extends axially along an axis through the case from the exterior side to the interior side. The interior side forms a peripheral boundary of an internal volume of the aircraft engine. A cavity is formed by and extends axially between the housing and the case. The component includes a projection and a mount that is disposed within the cavity. The projection projects axially out from the mount, through the aperture, and into the internal volume to a distal end of the component. The mount includes a rim and a plurality of spring beams. The spring beams bias the rim axially towards the case to provide a sealed engagement axially between the mount and the case.
Claims19
An assembly for an aircraft engine, comprising:
- a case including an aperture, an exterior side and an interior side, the aperture extending axially along an axis through the case from the exterior side to the interior side, and the interior side forming a peripheral boundary of an internal volume of the aircraft engine;
- a housing attached to the case, and a cavity formed by and extending axially between the housing and the case;
- and
- a component including a projection and a mount that is disposed within the cavity;
- the projection projecting axially out from the mount, through the aperture, and into the internal volume to a distal end of the component;
- the mount including a rim and a plurality of spring beams, the rim circumscribing the axis, the plurality of spring beams arranged circumferentially about the rim, each of the plurality of spring beams cantilevered from the rim, axially spaced from the case and axially engaging the housing such that the plurality of spring beams bias the rim axially towards the case to provide a sealed engagement axially between the mount and the case;
- and
- the housing including
- a housing interior side axially engaging the case;
- a passage;
- a counterbore projecting axially into the case from the housing interior side to the passage, wherein the rim is received within the counterbore;
- and
- a plurality of slots arranged circumferentially about the axis, each of the plurality of slots projecting radially within the housing out from the counterbore, and each of the plurality of slots projecting axially into the case from the housing interior side, wherein each of the plurality of spring beams is received within a respective one of the plurality of slots.
10 more elements
An assembly of an aircraft engine, comprising:
- a case including an aperture, a case exterior side and a case interior side, the aperture extending axially along an axis through the case from the case exterior side to the case interior side, and the case interior side forming a peripheral boundary of an internal volume of the aircraft engine;
- a fitting for a fluid conduit, the fitting mechanically fastened to the case, and a cavity formed by and extending axially between the fitting and the case;
- and
- a fluid intake including a projection and a mount that is arranged in the cavity;
- the projection projecting axially from the mount, through the aperture, and into the internal volume to an unsupported interior end of the fluid intake;
- and
- the mount including a rim, a first spring beam and a second spring beam, the rim circumscribing the axis and axially engaging the case, the first spring beam and the second spring beam arranged circumferentially about the rim and axially spaced from the case, the first spring beam projecting radially out from the rim to a distal radial end of the first spring beam, the first spring beam comprising a first standoff located at the distal radial end of the first spring beam, the first standoff biased axially against the fitting, the second spring beam projecting radially out from the rim to a distal radial end of the second spring beam, the second spring beam comprising a second standoff located at the distal radial end of the second spring beam, and the second standoff biased axially against the fitting.
4 more elements
An apparatus for an aircraft engine, comprising:
- an air intake including a projection, a mount, an air passage and an air inlet;
- the projection projecting axially along an axis out from an interior side of the mount to a distal end of the air intake;
- the mount including a rim, a first cantilevered spring beam and a second cantilevered spring beam, the rim extending circumferentially around the air passage and forming the interior side of the mount, and the first cantilevered spring beam and the second cantilevered spring beam arranged circumferentially about the rim and axially spaced from the interior side of the mount;
- the first cantilevered spring beam including a first leaf spring and a first standoff that is located at a distal radial end of the first cantilevered spring beam, the first leaf spring projecting radially out from the rim to the distal radial end of the first cantilevered spring beam, and the first standoff projecting axially out from the first leaf spring in an axial direction away from the distal end of the air intake to a distal axial end of the first standoff;
- the second cantilevered spring beam including a second leaf spring and a second standoff that is located at a distal radial end of the second cantilevered spring beam, the second leaf spring projecting radially out from the rim to the distal radial end of the second cantilevered spring beam, and the second standoff projecting axially out from the second leaf spring in the axial direction away from the distal end of the air intake to a distal axial end of the second standoff;
- the air passage projecting axially into the air intake through the mount and into the projection;
- and
- the air inlet formed in a sidewall of the projection and fluidly coupling the air passage to an environment outside of the air intake.
5 more elements
Dependencies are inferred from the claim text.