GAS TURBINE ENGINE SEAL ASSEMBLIES
First Claim
1. A gas turbine engine comprising:
- a shaft rotatable about an axis;
a bearing disposed about the shaft and within a bearing compartment;
a seal assembly positioned to seal the bearing compartment, the seal assembly comprising;
a fixed seal, anda seal runner rotatable with the shaft and having a first axial face and a second axial face axially opposite the first axial face with respect to the axis, wherein the first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion, a second surface angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface; and
an oil source positioned to provide oil into the trough portion.
4 Assignments
0 Petitions
Accused Products
Abstract
A gas turbine engine according to an example of the present disclosure includes a shaft rotatable about an axis, a bearing disposed about the shaft and within a bearing compartment, and a seal assembly positioned to seal the bearing compartment. The seal assembly includes a fixed seal and a seal runner rotatable with the shaft. The first axial face and a second axial face axially opposite the first axial face with respect to the axis. The first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion. A second surface is angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface. An oil source is positioned to provide oil into the trough portion.
-
Citations
20 Claims
-
1. A gas turbine engine comprising:
-
a shaft rotatable about an axis; a bearing disposed about the shaft and within a bearing compartment; a seal assembly positioned to seal the bearing compartment, the seal assembly comprising; a fixed seal, and a seal runner rotatable with the shaft and having a first axial face and a second axial face axially opposite the first axial face with respect to the axis, wherein the first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion, a second surface angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface; and an oil source positioned to provide oil into the trough portion. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
-
-
11. A gas turbine engine comprising:
-
a low pressure compressor; a high pressure compressor; a combustor in fluid communication with the lox pressure compressor and high pressure compressor; a low pressure turbine that drives the low pressure compressor; a high pressure turbine that drives the high pressure compressor through a shaft rotatable about an axis; a fan driven by the low pressure turbine; a bearing disposed about the shaft and within a bearing compartment between the high pressure compressor and the low pressure compressor, wherein the high pressure compressor includes an upstream-most stage of airfoils, and the bearing is disposed axially forward of the upstream-most stage relative to the flow of working fluid through the engine; a seal assembly positioned to seal the bearing compartment, the seal assembly comprising; a fixed seal, and a seal runner rotatable with the shaft and having a first axial face and a second axial face axially opposite the first axial face with respect to the axis, wherein the first axial face includes a first surface rotatable against the seal, and the second axial face includes a trough portion, a second surface angled relative to a radial baseline plane defined perpendicular to the axis, and a dam between the trough portion and the second surface; and an oil source positioned to provide oil into the trough portion. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20)
-
Specification