A bladed disc system for a turbine engine having a disk portion and a plurality of blade portions which are associated with a stator section and an intercavity sealing portion, disc portion shaped such that blade portions are able to fit within firtree slot in disc portion, blade portion having aerofoil section and root section, aerofoil section having portion shaped such that they extend proximate to intercavity sealing portion, disc portion extending from portion that connects with drum to outer edge at which blade portions are connected with disc portion having width transition region in which thickness of disc increases from point at which disc connects to drum to outer edge at which it holds blade portions, and wherein width transition region has curved width transition region with radius r, and an overhanging portion which extends into the intercavity spacing between the width transition region and the intercavity sealing portion.

A bladed disc system for a turbine engine, the bladed disk portion comprising a disk portion and a plurality of blade portions, the disc portion being shaped such that the blade portions are able to fit within fir tree slot in the disc portion, the blade portion comprising an aerofoil section and a root section, with the root section comprising a fir tree profile and a skirt portion and wherein the skirt portions of adjacent blades form an opening that has a maximum separation of between 1-50% of the maximum skirt opening width.

Rotor systems including an engine shaft, a forward hub, a rear hub, a rotor disk arranged between the forward hub and the rear hub, and a seal tube configured to define a forward hub compartment and a rear hub compartment. The forward hub compartment is defined forward of the rotor disk and the rear hub compartment is defined aft of the rotor disk. The seal tube is connected at a forward end to at least one of the rotor disk and the engine shaft and at a rear end to at least one of the rear hub and the engine shaft and the seal tube includes at least one axial compliance element configured to enable axial extension and compression of the seal tube in an axial direction along the engine shaft.

An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

A turbomachine is provided. The turbomachine includes a casing, a first airfoil disposed inside the casing such that a fluid passes through the first airfoil while flowing through the casing, a first inner frame coupled to a radially inner end of the first airfoil, a first inner wing protruding from the first inner frame in an axial direction of the casing, a second airfoil disposed inside the casing and between adjacent first airfoils in a flow direction of a fluid, a second inner frame coupled to a radially inner end of the second airfoil and disposed adjacent to the first inner frame, a second inner wing protruding from the second inner frame along the axial direction of the casing and disposed adjacent to the first inner wing, and a plurality of rim seals disposed between the first inner wing and the second inner wing, arranged at intervals along a circumferential direction of the casing, and configured such that cooling air present inside the first and second inner wings in a radial direction flows into each rim seal through an ingress port, passes through each rim seal, and flows out through an egress port, wherein a region on a downstream side of the first airfoil in the flow direction of the fluid flowing through the casing is divided into a first region having a relatively high pressure and a second region having a relatively low pressure, a first flow passage and a second flow passage are provided in a gap between each rim seal, the first flow passage is configured such that a size in the circumferential direction increases from the ingress port to the egress port and the egress port communicates with the first region, and the second flow passage is configured such that a size in the circumferential direction decreases from the ingress port to the egress port and the egress port communicates with the second region.

A turbofan engine has a primary duct , in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow , a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor The turbomachine further includes a cooling circuit extending between the compressor and the turbine.The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.

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 plurality of cooling passages extending in an axial direction are formed in a transition piece so as to be aligned in a circumferential direction and the axial direction. One or more downstream side passages are formed in a downstream side region (Rd) within one circumferential region. One or more upstream side passages are formed in an upstream side region Ru within the circumferential region. The total cross-sectional area per unit circumferential length of the one or more downstream side passages is larger than the total cross-sectional area per unit circumferential length of the one or more upstream side passages.

Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.

A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.