A seal for a gas turbine engine includes a top, a bottom, a left side, a right side, a back and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side. The top includes a first vane mating surface and the bottom includes a second vane mating surface.

The present invention relates to sealing element for sealing a radial gap relative to a counter element of a turbomachine, wherein the sealing element has a number of adjacent cells in the peripheral direction and/or in the axial direction, which are joined to one another by common walls, wherein an extension of a least one, in particular front-side, cross section of at least one cell in a first axial section of the sealing element in the peripheral direction and/or in the axial direction for sealing against a radial flange of the counter element is smaller than that in a second axial section of the sealing element that adjoins the first axial section upstream and/or in a second axial section that adjoins the first axial section downstream.

A turbomachine and a heat exchange system for the turbomachine are disclosed. The turbomachine includes a stationary component, a rotatable component, an abradable seal component, and a plurality of heat dissipating elements. The rotatable component includes teeth. The abradable seal component is operatively coupled to a surface of the stationary component and disposed facing the teeth to define a clearance there between the abradable seal component and the rotatable component. The plurality of heat dissipating elements is coupled to the abradable seal component. Each of the plurality of heat dissipating elements extends from the abradable seal component through the surface of the stationary component to a turbomachine cavity.

An abradable structure (10) for a turbomachine (40) that is designed to be at least partially deformed and/or at least partially abraded by at least one abrading element (44, 47) of the turbomachine (40) during operation thereof; the at least one abradable structure (10) being formed at least regionally of structural elements (12, 14, 16, 18) that have a respective polygonal cross section (20, 22) that is oriented in a rub direction (X_A) of the abradable structure (10). The structural elements (12, 14, 16, 18) have a greater extent (X.sub.h, X.sub.r) in the rub direction (X_A) than in a direction of the abradable structure (10) that is orthogonal to the rub direction (X_A). Other aspects of the present invention relate to a turbomachine (40) having an abradable structure (10), as well as to a method for manufacturing an abradable structure (10).

A sealing system (100) for a turbomachine is provided which includes a support (10) designed as a ring part, and a ring-like sealing plate (20, 30) that protrudes from the support in the axial direction (X). The support includes a fastening section (11) for fastening the sealing system to a stator part (200), and a retaining area (12), situated radially within the fastening section, for retaining a radial gap seal (40). The sealing plate (20, 30) is welded to the support (10) radially outside the retaining area (12). Also provided are a turbomachine that includes a sealing system (100), a support (10) for a sealing system, and a method for manufacturing a sealing system.

An air seal in a gas turbine engine comprising a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a soft ceramic material.

The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.

A rotating labyrinth seal especially useful for effecting sealing between two plenums in aircraft gas turbine engines comprising a base and a plurality of radially-directed seal teeth rings extending circumferentially around the outer peripheral surface of the base. The fins in the rotating seal each having a discontinuity that reduces hoop stress on the outer radial surface. The discontinuities in each fin are offset from the discontinuities in the adjacent fins.

A strain wave gearing is provided with a lubricant sealing structure that prevents a lubricant from leaking to the outside through a gap between a hollow input shaft and an end plate. The lubricant sealing structure is provided with a labyrinth seal that seals the gap. The labyrinth seal is configured by a plurality of gap portions defined by an oil-repellent surface in which fine grooves are formed in a prescribed groove array pattern. The oil-repellent surface is also formed at an outer peripheral surface portion on an upstream side of the labyrinth seal. Leakage of a lubricant oil to outside of the device can be reliably prevented through the oil-repellent effect of the oil-repellent surface at the upstream side, the sealing effect of the labyrinth seal, and the oil-repellent effect from the oil-repellent surface of the labyrinth seal.

A rotary machine includes a casing that is disposed on the outer circumference side of a rotating shaft and rotates about the axis relative to the rotating shaft, and a hole pattern seal that is fixed to the casing, divides a space between the rotating shaft and the casing into a high pressure side and a low pressure side, and has a first hole line on which a plurality of first hole portions are formed at intervals in a circumferential direction so as to face an outer circumferential surface of the rotating shaft. The hole pattern seal has fin portions that extend toward the rotating shaft at the high-pressure side of the first hole line and in the circumferential direction. The rotating shaft includes a convex portion that protrude from the outer circumferential surface of the rotating shaft toward the first hole portions to extend in the circumferential direction, and face the first hole portions at the low pressure side of the fin portion. The convex portion has a wall surface facing the fin portions.