An anti-vortex tube (AVT) retaining ring and bore basket is provided and includes a unitary body having an inboard portion, an outboard portion and an intermediate portion. The inboard portion includes a first ring-shaped body with an outer diameter. The outboard portion is configured to support an array of AVTs and includes a second ring-shaped body with an inner diameter larger than the outer diameter of the first ring-shaped body. The intermediate portion includes a flange extending between the outer and inner diameters of the first and second ring-shaped bodies, respectively.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk and a plurality of rotor blades. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. The first rotor blade includes an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk. The attachment has a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis. A portion of the first rotor disk extends circumferentially across and covers the attachment.

A rotor for a gas turbine engine has: a first rotor disk; an interstage flange that extends from the first rotor disk to a flange end portion that has an axial end surface and first radial outer and inner surfaces; a circumferential groove, formed in the flange end portion and extending from the axial end surface toward the first rotor disk; radial outer and inner slots formed in the first radial outer and inner surfaces along the circumferential groove and extend through the first radial outer and inner surfaces; and a valve member disposed within the circumferential groove and is secured within the circumferential groove when the flange end portion is connected to a second rotor disk, wherein the valve member deflects from rotor rotational speeds to seal or unseal the radial outer slot.

The present disclosure relates to a rotor assembly for a gas turbine engine, the rotor assembly comprising a first rotor stage having a first disc portion with a peripheral first rim portion and a second rotor stage, the second rotor stage having a second disc portion with a peripheral second rim portion. The second rotor stage is axially adjacent and downstream of the first rotor stage and the second rim portion has an axial extension extending towards the first rim portion such that the axial extension of the second rim portion defines a rotor drum cavity between the first and second disc portions. The second rotor stage further comprises a drive arm extending within the drum cavity to the first disc portion, the drive arm being connected to the first disc portion by at least one connector. The drive arm divides the drum cavity into radially outer rim cavity portion and a radially inner main cavity portion. The rotor assembly further comprises a rim seal located between the axial extension of the second rim portion and the first rim portion, and a pressure equalisation path extending from the rim cavity portion to the main cavity portion.

A turbopump includes an impeller (22) that is rotatable about an axis (A). A discharge collector (28) is located radially outward of the impeller. A passage (30) fluidly connects the impeller to the discharge collector. The passage is curved.

An impeller includes a plurality of pressurizing flow paths defined by a hub, a shroud, and vanes, the pressurizing flow paths being configured to cause fluid to flow in from a shaft direction of a turbine shaft, and cause the fluid to flow out toward an outer side in a radial direction of the turbine shaft, and the pressurizing flow paths being arranged in a row in a circumferential direction of the turbine shaft. Each of the pressurizing flow paths is a through hole having an inlet and an outlet and penetrating from the inlet to the outlet in a linear manner. The inlet is on an end surface of the impeller in the shaft direction of the turbine shaft. The outlet is on an outer circumferential surface of the impeller on an outer side in the radial direction of the turbine shaft.

A rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically to the rotor axis inside the rotor shaft. The rotor shaft further includes a plurality of cooling bores extending radially outward from the rotor cavity to feed cooling air into an internal cooling system in a blade. Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portion ends in a plateau, projecting above the outer circumference contour of the rotor cavity. Thus, cooling bore inlets are shifted to a low stress area and the lifetime of the rotor is improved.

A compressor rotor includes a first outer cavity formed in a rotor main body and into which air on a high-pressure side of blades is to be introduced, a first inner cavity formed in the rotor main body on an inner side in a radial direction of the first outer cavity; and a first communication passage which connects the first outer cavity and the first inner cavity to each other in the radial direction of the first outer cavity. Along an entire length of the first communication passage from the first outer cavity to the first inner cavity, the first communication passage is inclined toward a forward side of a rotation direction of the rotor main body.

The present disclosure relates to a rotor assembly for a gas turbine engine, the rotor assembly comprising a first rotor stage having a first disc portion with a peripheral first rim portion and a second rotor stage, the second rotor stage having a second disc portion with a peripheral second rim portion. The second rotor stage is axially adjacent and downstream of the first rotor stage and the second rim portion has an axial extension extending towards the first rim portion such that the axial extension of the second rim portion defines a rotor drum cavity between the first and second disc portions. The second rotor stage further comprises a drive arm extending within the drum cavity to the first disc portion, the drive arm being connected to the first disc portion by at least one connector. The drive arm divides the drum cavity into radially outer rim cavity portion and a radially inner main cavity portion. The rotor assembly further comprises a rim seal located between the axial extension of the second rim portion and the first rim portion, and a pressure equalisation path extending from the rim cavity portion to the main cavity portion.

A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.