A case for a gas turbine engine includes a case wall and a boss that extends from the case wall. The boss includes a perimeter step.

A holding device is used with a centripetal air sampling member of a rotor assembly that includes and downstream rotor discs and a centripetal air sampling member. The holding device has an annular support element with a housing configured to receive the air sampling member in a radial orientation, a first lateral extension, and a second lateral extension rigidly attached to the downstream rotor disc, extending substantially following the longitudinal axis and radially arranged externally with respect to the first extension. The holding device also includes a wedging ring axially arranged between a portion of the downstream rotor disc and the support element, the wedging ring being configured to simultaneously urge, under the action of a centrifugal force, the first extension in radial abutment against the second extension and the support element in radial abutment against a portion of the upstream rotor disc.

A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.

A sealing washer for use in a rotor of a gas turbine, sealing being brought about on one side of the sealing washer by an approximately radially oriented bearing face and on the other side by way of a supporting face which is oriented in an inclined manner with respect to the rotor axis. The sealing washer is of split configuration and has at least one washer segment with a circumferential washer section. At the dividing point, a pressing section and a triangular section overlap along a dividing face. Here, the dividing face intersects the bearing face and makes sealing both with the pressing section and with the triangular section possible. In order to also make sealing on the supporting face with the pressing section and the triangular section possible, the triangular section is reduced to at most 0.3 times the cross-sectional area of the washer section.

There is provided a seal assembly comprising: a first component and a second component spaced apart from the first component so as to define a passage for the transfer of fluid from an inlet of the seal assembly to an outlet of the seal assembly, wherein the first component comprises a concavity at least partially defining the passage, and wherein no part of the second component extends into the portion of the passage bounded by the concavity.

The present invention relates to a labyrinth seal for a turbine engine, in particular of an aircraft, comprising a rotor element and a stator element extending around the rotor element, the rotor element being suitable for rotating relative to the stator element about an axis of rotation having an axial direction (DA), the rotor element comprising an annular lip having an outer radial end extending towards an abradable element (57) carried by the stator element, the outer radial end of the annular lip having a corrugation in the axial direction (DA) and a non-zero axial expanse (E.sub.5) associated with the corrugation, the abradable element (57) comprising a plurality of cells (50a, 50b) arranged adjacent to one another along the axial direction (DA) and an ortho-radial direction (O), the cells (50a, 50b) comprising walls which extend in an essentially radial direction, the cells being distributed with a first cell density in a first densified annular zone (Z.sub.51) of the abradable element, said densified annular zone (Z.sub.51) being located opposite the radial end of the lip, said densified annular zone having an axial expanse less than or equal to the axial expanse of the outer radial end of the lip, the cells being distributed according to a reference density of cells outside said first zone, the first density being greater than the reference density.

A rotating machine includes a casing having a hollow shape; a rotator rotatably supported in the casing; a stator blade fixed to an inner peripheral portion of the casing; a rotor blade fixed to an outer peripheral portion of the rotator while being displaced from the stator blade in an axial direction of the rotator; a sealing device disposed between the inner peripheral portion of the casing and a tip of the rotor blade; a swirling flow generation chamber provided along a circumferential direction of the rotator on a downstream side of the sealing device in the casing in a fluid flow direction; and guiding members provided at predetermined intervals in the swirling flow generation chamber in the circumferential direction of the rotator. The guiding members each include a first guiding surface that is inclined in the circumferential direction with respect to the axial direction of the rotator.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly, a blade assembly and a method for installing a locking spacer assembly into a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly are presented. The locking spacer assembly includes a first side piece, a second side piece, a bolt and a mid piece. The mid piece includes a hollow cylindrical body to receive the bolt and a top platform to flush with top surfaces of the first and second side pieces and a middle platform disposed at bottom of the hollow cylindrical body. At least two pins are radially inserted through apertures of the first and second side pieces respectively extending toward the middle platform of the mid piece to prevent radial movement of the mid piece.

A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall including adjacent bounding pedestals that extend from an external wall surface to establish a cooling passage, and including a common pedestal situated between the adjacent bounding pedestals to establish a first branched section and a second branched section of the cooling passage that join together at a merged section of the cooling passage. A method of fabricating a gas turbine engine component is also disclosed.

The present invention relates to a method for producing an engine component having a cooling duct arrangement which has a plurality of cooling ducts, each having an inflow opening, the inflow openings being arranged according to a predefined pattern in an inflow surface of the engine component, and each cooling duct opening into a recess in a wall of the engine component, along which wall a cooling film is to be formed. According to the invention, the pattern is formed in at least one subregion of defined size of the inflow surface, from a plurality of identical isosceles triangles, which are defined by a minimum spacing (k) and by a mean diameter (a) of the inflow openings correlating to the minimum spacing (k). This procedure reduces the complexity of the design process.