Combined rotating component and fluid port baffle
AssigneePratt & Whitney Canada Corp.
InventorCedric Chan Chuen
Life of this patent
Estimating the term…
Abstract
An aircraft engine has a gearbox having a casing defining an internal chamber and a scavenge port. A gear is rotatably mounted inside the internal chamber for rotation about a rotation axis. The gear is axially spaced from the scavenge port. A baffle is disposed inside the internal chamber. The baffle includes a perforated plate disposed radially between the gear and the scavenge port relative to the rotation axis. The perforated plate has a first portion extending around a portion of a circumference of the gear, and a second portion extending axially away from the first portion over the scavenge port of the scavenge area.
Claims17
A gearbox of an aircraft engine, comprising:
- a casing defining an internal chamber having a scavenge area, the scavenge area having a scavenge port for scavenging lubricant from the internal chamber;
- a gear rotatably mounted inside the internal chamber for rotation about a rotation axis, the gear axially spaced from the scavenge port along the rotation axis;
- and
- a baffle inside the internal chamber, the baffle including a perforated plate disposed radially between the gear and the scavenge port relative to the rotation axis, the perforated plate having a first portion extending around a portion of a circumference of the gear, and a second portion extending axially away from the first portion over the scavenge port of the scavenge area;
- wherein the first portion and the second portion of the perforated plate extend in a cantilevered fashion from opposed sides of a web portion, the web portion having two or more mounting points to the casing, and wherein the web portion is disposed at an axial location between the gear and the scavenge port.
A gearbox of an aircraft engine, comprising:
- a casing defining an internal chamber having a scavenge port;
- a gear disposed inside the internal chamber for rotation about a rotation axis, the gear axially spaced from the scavenge port along the rotation axis and disposed at a higher elevation than the scavenge port;
- and
- a baffle supported within the internal chamber at an elevation comprised between the gear and the scavenge port, the baffle having a perforated plate axially spanning both the gear and the scavenge port:
- wherein the perforated plate is supported via a web projecting from the perforated plate towards the rotation axis, the web disposed axially between the gear and the scavenge port.
An oil scavenge system of an aircraft engine, comprising:
- a casing defining an internal chamber about a rotation axis of a rotating component, the internal chamber confining oil in motion within the casing and defining a scavenge area below the rotation axis, the scavenge area having a scavenge port at a bottom of the casing;
- and
- a baffle disposed within the internal chamber and located in the scavenge area, the baffle having an inverted T-shaped cross-section comprising a perforated plate at a lower end of a web projecting from an intermediate location of the perforated plate towards the rotation axis, the web disposed axially between the rotation component and the scavenge port and axially facing an axially facing surface of the rotating component, the perforated plate axially spanning both the rotating component and the scavenge port.
Dependencies are inferred from the claim text.