Cover for rotatable shaft of gas turbine engine
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a rotatable shaft and a cover substantially covering an end of the rotatable shaft. The cover includes a passageway fluidly coupled from outside the shaft to inside the shaft. The cover further includes a fin configured to prevent oil from entering the passageway.
1. A cover configured to cover substantially an entire end of a rotatable shaft of a gas turbine engine, comprising:
a passageway fluidly coupled from a first side of the cover to a second side of the cover; and
a fin configured to prevent oil from entering the passageway;
wherein the cover includes a hub projecting from a wall,
wherein the passageway includes an axial section extending into the hub along an axis, and
wherein the passageway includes a plurality of radial sections formed in the hub and extending in a direction substantially perpendicular to the axis between the axial section and an outer diameter of the hub,
wherein the outer diameter of the hub provides the fin,
wherein the outer diameter of the hub adjacent the fin has a greater radial dimension than the outer diameter of the hub adjacent the plurality of radial sections,
wherein the fin is axially between the plurality of radial sections and the inner surface of the wall,
wherein the fin is a first fin and the hub further includes a second fin,
wherein the radial sections are axially between the first and second fins,
wherein the outer diameter of the hub provides a first channel between the first fin and the inner surface of the wall and a second channel between the first and second fins,
wherein the first and second channels are substantially concave from a radially outer perspective, and
wherein bases of the first and second channels are defined by respective radii having origins on a centerline of a respective one of the first channel and the second channel.
2. A gas turbine engine, comprising:
a rotatable shaft; and
a cover substantially covering an end of the rotatable shaft, the cover including a passageway fluidly coupled from outside the rotatable shaft to inside the rotatable shaft, the cover further including a fin configured to prevent oil from entering the passageway,
wherein the cover includes a wall covering substantially the entire end of the rotatable shaft,
wherein the wall includes an outer surface facing outside the rotatable shaft and an inner surface facing inside the rotatable shaft,
wherein the cover includes a hub projecting from the inner surface of the wall,
wherein the passageway includes an axial section extending along an engine central longitudinal axis from the outer surface to a location within the hub,
wherein the passageway includes a plurality of radial sections extending in a direction substantially perpendicular to the engine central longitudinal axis between the axial section and an outer diameter of the hub,
wherein the outer diameter of the hub provides the fin,
wherein the outer diameter of the hub adjacent the fin has a greater radial dimension than the outer diameter of the hub adjacent the plurality of radial sections,
wherein the fin is axially between the plurality of radial sections and the inner surface of the wall,
wherein the fin is a first fin and the hub further includes a second fin,
wherein the radial sections are axially between the first and second fins,
wherein the outer diameter of the hub provides a first channel between the first fin and the inner surface of the wall and a second channel between the first and second fins,
wherein the first and second channels are substantially concave from a radially outer perspective, and
wherein bases of the first and second channels are defined by respective radii having origins on a centerline of a respective one of the first channel and the second channel.
3. A gas turbine engine, comprising:
a rotatable shaft; and
a cover substantially covering an end of the rotatable shaft, the cover including a passageway fluidly coupled from outside the rotatable shaft to inside the rotatable shaft, the cover further including a fin configured to prevent oil from entering the passageway,
wherein the cover includes a wall covering substantially the entire end of the rotatable shaft,
wherein the wall includes an outer surface facing outside the rotatable shaft and an inner surface facing inside the rotatable shaft,
wherein the cover includes a hub projecting from the inner surface of the wall,
wherein the passageway includes an axial section extending along an engine central longitudinal axis from the outer surface to a location within the hub,
wherein the passageway includes a plurality of radial sections extending in a direction substantially perpendicular to the engine central longitudinal axis between the axial section and an outer diameter of the hub,
wherein the outer diameter of the hub provides the fin,
wherein the outer diameter of the hub adjacent the fin has a greater radial dimension than the outer diameter of the hub adjacent the plurality of radial sections,
wherein the fin is axially between the plurality of radial sections and the inner surface of the wall,
wherein the fin is a first fin and the hub further includes a second fin,
wherein the radial sections are axially between the first and second fins,
wherein the outer diameter of the hub provides a first channel between the first fin and the inner surface of the wall and a second channel between the first and second fins,
wherein centerlines of the radial sections are concentric with a centerline of the second channel, and
wherein the second channel includes a raised center section such that a minimum radial dimension of the outer diameter of the hub is spaced-apart from the centerline of the second channel.
4. The gas turbine engine as recited in claim 3 , wherein the hub is concentric with an engine central longitudinal axis.