Pratt-whitney Canada Corp

Hugo Quintin

Michel Labbe

Rose-Elizabeth Banville

Sebastien Gagne

Cedric Chan Chuen

An assembly includes a rotating seal land, a seal element, a stationary seal support and a mating plate. The seal element axially overlaps, circumscribes and radially sealingly engages the rotating seal land. The stationary seal support axially overlaps and circumscribes the rotating seal land and the seal element. The stationary seal support includes a support notch, a support shoulder, a support inner interior surface and a support outer interior surface. The support notch projects axially into the stationary seal support from a distal end of the stationary seal support to the support shoulder. The support notch projects radially outward away from an axis into the stationary seal support from the support inner interior surface to the support outer interior surface. The mating plate is seated in the support notch and mounted to the stationary seal support. The mating plate axially contacts the support shoulder and the seal element.

Seal assembly mating plate for aircraft powerplant

A bearing system for supporting a shaft, comprising: a bearing including: an inner race about an axis, the inner race having an interior coupled to the shaft; rolling elements about the axis and around the inner race; and an outer race about the axis and around the rolling elements; a housing having a cavity defining an axial location relative to the axis, the bearing received by the cavity; a first axial loading structure in the cavity and operatively connected to the bearing; and a second axial loading structure in the cavity extending axially away from the axial location in a first axial direction, the second loading structure opposing movement of the bearing relative to the axial location in a second axial direction when the bearing loads the second axial loading structure in the second axial direction, the first and second axial loading structures operationally independent from one another.

Loaded bearing system

An aircraft engine, has: a shaft rotatable about a central axis and engaged at an end thereof to a rotatable load via splines; a reference tube extending around the shaft and having a first end secured to the shaft and a second end free relative to the shaft for measuring a deformation of the shaft, the reference tube defining at least one tube aperture; an oil nozzle defining an exit flow axis intersecting the at least one tube aperture, the shaft defining at least one shaft aperture through the shaft, an oil flow path extending from the oil nozzle to the splines; and a drain outlet located radially outwardly of an inlet of the at least one shaft aperture for outputting excess oil out of an annular gap defined between the shaft and the reference tube.

Growing community of inventors

Varennes, Canada

Hugo Quintin