An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.

A component is provided for an aircraft. This aircraft component includes an object and a multi-layer coating. The object includes an object surface. The multi-layer coating includes a barrier layer and a laminar flow layer. The covers at least a portion of the object surface. The barrier layer a fluoropolyether, a silicon rubber and/or a polyurethane. The laminar flow layer covers the barrier layer and forms an exterior surface of the component. The laminar flow layer includes a sol-gel siloxane, a rare-earth oxide and/or a phosphate.

Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm.sup.2, and an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

A ring-shaped compliant support for a gas turbine engine includes, among other things, an annular case, and an adjustment member that will turn relative to the annular case if exposed to thermal energy.

An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one of the axial faces defines a buffer cavity into which a wing extends from the other of the axial faces and having a surface confronting the fluid outlet. A flow reverser is further provided within at least one of the surface or the terminal portion of the other of the axial faces.

A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.

A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount.

A catch assembly is provided that includes a keeper, a guide and a catch. The catch includes a catch mount, a catch arm and a catch hook. The catch arm is cantilevered from the catch mount. The catch arm extends longitudinally away from the catch mount to a distal end of the catch. The catch hook is connected to the catch arm at the distal end. The catch is configured to bias the catch hook against the guide. The catch hook is configured to slide longitudinally along the guide from a first position to a second position where the catch hook engages the keeper.

A guide vane assembly of an aircraft turbine engine, the guide vane assembly being segmented into a plurality of segments arranged circumferentially next to one another about an axis. The guide vane assembly includes two annular rings connected together by vanes and the geometry of the inner ring is modified to reduce the vibrational responses of the guide vane assembly

In a vacuum pump, a spiral plate on a downstream side of a slit is not disposed on an extended line of a spiral plate on an upstream side of the slit but is disposed after in a direction in which a gap formed by the slit is reduced. The distance by which the downstream spiral plate is moved corresponds to the distance in which the gap disappears and the upstream spiral plate and the downstream spiral plate overlap. When scraping the spiral plates, the radius of a machining end mill is set smaller than the width of the slit of the spiral plate, and the radius of the machining end mill is set smaller than the phase difference between the upstream spiral plate and the downstream spiral plate. In addition, end portions of the spiral plates between which the slit is formed are subjected to chamfering.