A variable nozzle device 20 for a variable geometry turbocharger includes: a nozzle mount 21; a nozzle plate 22 disposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passage 4 having an annular shape between the nozzle plate 22 and the nozzle mount 21; and a plurality of variable nozzle vanes 6 disposed at a predetermined interval in a circumferential direction of the nozzle flow passage 4 so as to be individually rotatable about a pivot axis 02. The nozzle plate 22 includes a first surface 33 facing the nozzle mount 21, a second surface 34 opposite to the first surface 33, and at least one through hole 36 formed through the first surface 33 and the second surface 35. The at least one through hole 36 has a first opening 36a formed on the first surface 33 at an inner side of the pivot axis with respect to a radial direction, and a second opening 36b formed on the second surface 35 at an outer side of the first opening 36a with respect to the radial direction or at the same position as the first opening 36a with respect to the radial direction. Accordingly, as the working fluid ‘g’ injected from the through hole 36 joins the working fluid G flowing through the nozzle flow passage 4 toward the turbine wheel 3 through the plurality of variable nozzle vanes 6, the flow of the working fluid G is guided toward the inner surface at the hub 32 side, and thereby it is possible to suppress deviation of flow of the working fluid G toward the shroud, that is, suppress the drift of the working fluid G.

A device for holding (101) at least one cooling tube (120) of a turbomachine casing (10) cooling system (100), the holding device including a fixing frame (104), a holding member (160) being configured to hold two cooling tubes (120), and a connection assembly (140) between the holding member (160) and a fixing frame (104), extending on either side of the frame, the connection assembly (160) comprising a connection part (150) extending through an opening (108) of the fixing frame from an outer portion (141) to the inner portion (142) of the connection assembly, the inner portion (142) being disposed between two cooling tubes (120) and secured to the holding member (160) while the outer portion (141) comprises a resilient return member (170) urged in compression towards the fixing frame by the connection part (150).

The invention relates to an annular assembly for a dual-flow turbomachine having a longitudinal axis (A) and comprising a casing (12) with an annular shell (14), one face of which supports a piece of annular equipment, a plurality of means of attachment (18) for attaching the equipment to the annular shell (14) being distributed around the longitudinal axis (A) and allowing the equipment (16) a degree of freedom in the tangential direction relative to the annular shell (14), characterised in that each means of attachment (18) comprises a rail (20) integral with the annular equipment (16) and arranged radially between a first radially internal plate (22) and a second, radially external plate (24) and capable of sliding in the tangential direction between the first plate (22) and the second plate (24), and in that a removable support element (56) is securely connected to the annular shell and to the first plate (22) and second plate (24).

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

An apparatus has: a first member; a shaft rotatable relative to the first member about an axis; and a seal system. The seal system has a seal carrier having: an axially-extending wall having an inner diameter (ID) surface; and a radially-extending wall having a first surface. A seal is carried by the first member and has: an outer diameter (OD) surface; and a seal face. A seat is carried by the shaft and has a seat face in sliding sealing engagement with the seal face. One or more springs bias the seal carrier relative to the first member so as to bias the seal face against the seat face. At least one of the seal carrier inner diameter (ID) surface and seal outer diameter (OD) surface is formed by a coating.

Turbomachine ring as well as a turbomachine comprising such a ring and a method for repairing such a ring, the turbomachine ring comprising an essentially cylindrical support, including a frontal surface wherein a notch is formed, one or more sectors forming an annulus configured to embody a segment of air stream, each sector comprising a hook portion protruding in the direction of the support and engaging in the notch of the support, and an anti-wear device having a U shaped portion, provided in the notch of the support and pressed at least against the radially external surface of the notch, and a tab portion, continuously extending the U shaped portion, pressed and fastened against the frontal surface of the support.

A disk spring may include an annular base body, a central longitudinal axis of which defines an axial direction of the base body. A profile of the base body in a profile plane containing the central longitudinal axis may have a wave-shaped contour with two minima including a radially inner minimum and a radially outer minimum and with an intermediate maximum disposed between the two minima. The wave-shaped contour may extend from a radially inner end point to a radially outer end point. The radially inner end point may be arranged offset in the axial direction with respect to the radially outer end point.

A rotor blade is provided. The rotor blade includes a main body having a shank, an airfoil extends radially outwardly from the shank, and a platform. The main body includes a pressure side slash face and a suction side slash face. A slot is defined within each of the pressure side slash face and the suction side slash face. The slot of the pressure side slash face and the slot of the suction side slash face each include an upstream end portion that defines an end and a main body portion extending from the upstream end portion. The upstream end portion tapers from the end to the main body portion. The main body portion further includes a retention wall that covers a portion of the end and that defines an opening. The retention wall further includes an inner retention surface. The retention wall defines an offset from the opening.

A fan receiver assembly (1200) includes a fan receiver (101). The fan receiver includes a rear wall (128) and at least one sidewall (112). At least one deformable clasp (105) is coupled to, and translatable along, the sidewall. The deformable clasp includes at least one latching arm (142) that is pivotable between an axially displaced open position occurring when the latching arm extends beyond a terminal end sidewall and a parallel position occurring when the latching arm is situated between the terminal end and the rear wall. The sidewall defines a d-track (111) having a terminal end (125) and an outward notch (126). A follower situates within the d-track between the deformable clasp and the sidewall. A fan module (102) latches to the fan receiver assembly when the follower situates within the outward notch.

A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. The system also includes a bladder positioned between the outer platform of the stator and the case and designed to receive pressurized fluid having a greater pressure than ambient pressures experienced at the low pressure side of the stator and to further resist movement of the stator relative to the case in response to receiving the pressurized fluid.