In a flange cooling structure of a gas turbine engine, one of a first flange and a second flange is a high pressure flange that faces a first region, and the other of the first flange and the second flange is a low pressure flange that faces a second region. A contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.

A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.

An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

A sealing device includes a fin, a through hole, and a high pressure fluid supplying unit. The fin extends from a stationary body toward a rotating body in a gap between the stationary and rotating bodies. The fin is not in contact with the rotating body. The through hole is formed to be opened in at least one of the stationary body and the rotating body on an upstream side of the fin in a flow direction of a fluid to flow into the gap between the stationary body and the rotating body. The through hole is opened toward an upstream side of the fluid to flow in the gap between the stationary body and the rotating body. The high pressure fluid supplying unit is configured to supply a high pressure fluid to the gap from the through hole. The high pressure fluid has a higher pressure than the fluid.

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

A turbine blade having a base and an airfoil, the base including cooling air inlets and an internal cooling air passageway, and the airfoil including an internal multi-bend heat exchange path beginning at the base and ending at a cooling air outlet at the trailing edge of the airfoil. The airfoil also includes a skin that encompasses a tip wall, an inner spar, and a tip flag cooling system.

A device cools a disk of a turbine extending along an axis. The disk includes on its circumference at least one recess surrounded by disk teeth each having an upstream face. The recess includes a bottom in fluid communication with an upstream cavity by way of at least one lunula. The lunula includes lateral surfaces that are inclined with respect to the radial plane which constitutes the plane of symmetry of the recess into which the lunula opens.

A compressor section or a turbine section of a gas turbine engine having an axis includes a drum. The compressor section or the turbine section also includes a plurality of bores extending radially inward from the drum including a first bore and a second bore. The compressor section or the turbine section also includes a first bore basket at least partially defining a first cavity such that the first bore has at least one surface located in the first cavity. The compressor section or the turbine section also includes a second bore basket at least partially defining a second cavity that is isolated from the first cavity such that the second bore has at least one surface located in the second cavity.

The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A system for separating debris includes a first separation device in fluid communication with an inlet flow path of a compressor and a second separation device in fluid communication with an outlet flow path of the compressor and an inlet flow path of a combustor. The first separation device is adapted to remove coarse particles from the airflow. The second separation device is adapted to remove fine particles from the airflow. The course particles have a larger mean particle diameter than the fine particles.

A moving blade of a turbo machine, having a leading edge, a flow trailing edge, flow conduction faces, and a blade root mounting the moving blade to a hub body. The blade root is fir tree-like with projections spaced apart from one another. An inner shroud is arranged between the blade leaf and the blade root. A cooling passage is integrated in the blade leaf and the blade root for a cooling medium. An inlet of the cooling passage is formed on the blade root formed of a first inlet passage portion and a second inlet passage portion and a material web extends there between. The first inlet passage portion and the second inlet passage portion merge into a unifying passage portion arranged radially outside the uppermost projection of the blade root and radially inside of the inner shroud.