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US 2026/0077873 A1Published application
Assembly and method for connecting aircraft components together
AssigneePratt & Whitney Canada Corp.
InventorsStephane Gignac, Joanna Radon
Life of this patent
Estimating the term…
Abstract
An assembly is provided for an aircraft. This aircraft assembly includes a fluid reservoir structure, an aircraft engine housing structure and a mounting assembly. The fluid reservoir structure includes a first mount. The aircraft engine housing structure includes a second mount. The mounting assembly connects the first mount to the second mount while providing controlled intercomponent movement between the first mount and the second mount to reduce internal stress and/or wear. The mounting assembly includes a first bushing, a second bushing and a fastener.
Claims20
An assembly for an aircraft, comprising:
- a fluid reservoir structure comprising a first mount, the first mount comprising a first mount aperture that extends axially along an axis through the first mount from a first mount first side to a first mount second side;
- an aircraft engine housing structure comprising a second mount, the second mount comprising a second mount aperture that extends axially along the axis through the second mount from a second mount first side to a second mount second side;
- and
- a mounting assembly connecting the first mount to the second mount while providing controlled intercomponent movement between the first mount and the second mount to reduce internal stress and/or wear, the mounting assembly including a first bushing, a second bushing and a fastener;
- the first bushing including a first bushing bore, a first bushing base and a first bushing rim that projects radially out from the first bushing base, the first bushing base projecting partially axially into the first mount aperture without contacting the second bushing, and the first bushing rim axially next to the first mount first side;
- the second bushing including a second bushing bore, a second bushing base and a second bushing rim that projects radially out from the second bushing base, the second bushing base projecting partially axially into the second mount aperture, and the second bushing rim axially next to and between the first mount second side and the second mount first side;
- and
- the fastener projecting axially through the first bushing bore and the second bushing bore.
5 more elements
An aircraft assembly for providing controlled intercomponent movement to reduce internal stress and/or wear, the aircraft assembly comprising:
- a shoulder fastener including a head, a shoulder section and a threaded section, the shoulder section projecting axially along an axis from the head to the threaded section;
- a first bushing having a first bushing axial thickness that extends axially from a first bushing first end to a first bushing second end, the first bushing including a first bushing base and a first bushing rim disposed at the first bushing first end, the first bushing base mounted on the shoulder section, and the first bushing rim projecting radially out from and circumscribing the first bushing base;
- a second bushing having a second bushing axial thickness that extends axially from a second bushing first end to a second bushing second end, the second bushing including a second bushing base and a second bushing rim disposed at the second bushing first end, the second bushing base mounted on the shoulder section, the second bushing rim projecting radially out from and circumscribing the second bushing base, the second bushing first end located axially next to the first bushing second end, and the second bushing second end located axially next to the head;
- a nut threaded onto the threaded section;
- and
- a washer clamped between the nut and an axial end of the shoulder section, the washer axially next to the first bushing first end, wherein an axial distance extending from the washer to the head is greater than a sum of the first bushing axial thickness and the second bushing axial thickness.
3 more elements
A method for attaching components together while providing controlled intercomponent movement to reduce internal stress and/or wear, the method comprising:
- inserting a base of a first bushing into an aperture in a first mount with a rim of the first bushing axially engaging the first mount, the first mount having a first mount axial thickness, and the rim of the first bushing having a first bushing rim axial thickness;
- inserting a base of a second bushing into an aperture in a second mount with a rim of the second bushing axially engaging the second mount, the second mount having a second mount axial thickness, and the rim of the second bushing having a second bushing rim axial thickness;
- inserting a shoulder section of a fastener through a bore of the first bushing and a bore of the second bushing, a head of the fastener axially next to the second mount, and the rim of the second bushing axially next to the first mount;
- determining a stack dimension, the stack dimension equal to a sum of the first mount axial thickness, the first bushing rim axial thickness, the second mount axial thickness and the second bushing rim axial thickness;
- selecting a washer out of a set of washers with different configurations based on the stack dimension;
- mounting the washer on a threaded section of the fastener, the washer axially next to the first bushing;
- and
- threading a nut onto the threaded section of the fastener to axially clamp the washer between the nut and an axial end of the shoulder section of the fastener.
5 more elements
Dependencies are inferred from the claim text.