Mtu Aero Engines Ag

Alexander Kloetzer

Manfred Feldmann

Werner Humhauser

Herman Klingels

Dieter Hofmann

A component joint including a turbomachine component () having at least one component flange (); a mating turbomachine component () connected thereto and having at least one mating component flange (); and at least one seal () to provide a seal against an overpressure (p&#x2212;p) on the component side, the at least one seal () having a sealing surface () that engages into a groove () of the turbomachine component (), the groove () being disposed on a mating-component-flange-facing side of the component flange () and having a contact surface () for sealingly axially supporting the sealing surface ().

Component joint

A fastening assembly having a component flange (), in particular of a turbomachine, having at least one bore () in which a sleeve () is placed that extends through a bolt () which has a head () that is axially secured between a rim () of the bore and a component flange-mounted axial limit stop ().

Fastening assembly

The invention is directed to a seal arrangement, in particular a brush seal, for a turbine, in particular an aircraft gas turbine, with a sealing element and with a sealing surface that interacts with the sealing element, wherein the sealing element and the sealing surface are arranged concentrically with respect to each other, in particular concentrically around a machine axis of the turbine is hereby characterized in that the sealing element and the sealing surface are designed in such a way that, in a first operating state, a gap is formed between them, and in that, in a second operating state, a sealing contact is produced between the sealing element and the sealing surface.

Seal arrangement for turbine

The present invention relates to an arrangement, comprising a first turbomachine element with a first turbomachine element through-opening, a second turbomachine element, a sliding element with a sliding element through-opening that is arranged, at least in part, in the first turbomachine element through-opening, a sleeve that engages through the sliding element through-opening along a through-axis, and a fastening member that engages through the sleeve for fastening the sleeve to the second turbomachine element. Furthermore, the invention relates to a method for fastening the first turbomachine element to the second turbomachine element, a turbomachine with the above-mentioned arrangement, and use of this arrangement.

Arrangement for joining elements of turbomachines

A seal carrier for a turbomachine, in particular a gas turbine, including a carrier base and at least one seal member, the at least one seal member being connected to the carrier base, and the at least one seal member being formed by a plurality of cavities arranged adjacent one another, in particular in a regular fashion, in the circumferential direction and the axial direction, the cavities extending from the carrier base in the radial direction, is provided. At least one stiffening element on the carrier base, the stiffening element extending along the circumferential direction and at least partially covering the at least one seal member at one of its axial end regions is provided.

Seal carrier for a turbomachine, in particular a gas turbine

A rotor of a turbomachine. The rotor includes at least one blade () that has a blade leaf () and a blade root (), and a rotor base body (), in particular a disk (), that has an outwardly open, circumferential groove () for receiving the blade root (). The circumferential groove () and the blade root () are shaped in a way that allows the blade root () to be secured in the circumferential groove () by the rotation of the blade () about an axis (A, A).

Rotor of a turbomachine

A blade-disk assembly of a turbomachine is provided, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. A method for assembling such a blade-disk assembly, as well as a turbomachine, is also provided.

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Fuerstenfeldbruck, Germany

Alexander Kloetzer