Abstract: A gas turbine engine includes, among other things, a bearing compartment, a shaft configured to rotate during operation of the gas turbine engine, and a sleeve configured to rotate with the shaft during operation of the gas turbine engine. The sleeve includes a variable radial dimension about a circumference of the sleeve. The engine further includes a seal statically mounted relative to the sleeve and configured to cooperate with the sleeve to seal the bearing compartment.

Abstract: An assembly for rotational equipment includes a scoop ring body. The scoop ring body extends radially between and to an inner radial side and an outer radial side. The scoop ring body extends axially between and to a first axial side and a second axial side. The scoop ring body forms at least one scoop including a passage, an inner channel, and at least one axial passage. The passage extends through the scoop ring body from an inlet to an outlet. The inner channel extends along the inner radial side between and to an upstream channel end and a downstream channel end. The upstream channel end is disposed at the outlet. The at least one axial passage extends through the scoop ring body from a passage inlet to a passage outlet. The passage inlet is disposed at the inner channel and the passage outlet is disposed at the first axial side or the second axial side.

Abstract: An assembly for rotational equipment includes a scoop ring body and an insert. The scoop ring body is rotatable about a rotational axis. The scoop ring body extends radially between and inner radial side and an outer radial side. The scoop ring body includes a body material. The insert is mounted to the scoop ring body. The insert includes an insert material and a cutting edge. The insert material is different than the body material. The scoop ring body and the insert form a passage. The passage extends through the scoop ring body from an inlet at the outer radial side to an outlet at the inner radial side. The cutting edge is at the inlet. The passage extends within the scoop ring body between a first circumferential side and a second circumferential side. The passage at the first circumferential side is at least partially formed by the insert.

Abstract: An assembly for rotational equipment includes a scoop ring body and an insert. The scoop ring body is rotatable about a rotational axis. The scoop ring body extends radially between and inner radial side and an outer radial side. The scoop ring body includes a body material. The insert is mounted to the scoop ring body. The insert includes an insert material and a cutting edge. The insert material is different than the body material. The scoop ring body and the insert form a passage. The passage extends through the scoop ring body from an inlet at the outer radial side to an outlet at the inner radial side. The cutting edge is at the inlet. The passage extends within the scoop ring body between a first circumferential side and a second circumferential side. The passage at the first circumferential side is at least partially formed by the insert.

Abstract: A gas turbine engine includes, among other things, a bearing compartment, a shaft configured to rotate during operation of the gas turbine engine, and a sleeve configured to rotate with the shaft during operation of the gas turbine engine. The sleeve includes a variable radial dimension about a circumference of the sleeve. The engine further includes a seal statically mounted relative to the sleeve and configured to cooperate with the sleeve to seal the bearing compartment.

Abstract: A gas turbine engine includes, among other things, a bearing compartment, a shaft configured to rotate during operation of the gas turbine engine, and a sleeve configured to rotate with the shaft during operation of the gas turbine engine. The sleeve includes a variable radial dimension about a circumference of the sleeve. The engine further includes a seal statically mounted relative to the sleeve and configured to cooperate with the sleeve to seal the bearing compartment.

Abstract: A gas turbine engine includes, among other things, a bearing compartment, a shaft configured to rotate during operation of the gas turbine engine, and a sleeve configured to rotate with the shaft during operation of the gas turbine engine. The sleeve includes a variable radial dimension about a circumference of the sleeve. The engine further includes a seal statically mounted relative to the sleeve and configured to cooperate with the sleeve to seal the bearing compartment.