Siemens Aktiengesellschaft

Siemens Akteingesellschaft

Armin Hülfenhaus

Claus Vögelin

Johann Floter

Harald Hoell

Giuseppe Gaio

Dieter Brillert

Marcus Brücher

Frank Günther

Gerhard Hülsemann

Hajrudin Ceric

Andreas Föhrigen

Sabine Rintzel

Melanie Uckert

Uwe Wegmann

Gabriel Jungnickel-Marques

Stefan Wanz

Carsten Foerster

Gang Yi Li

Christian Bäumler

Detlef Gruhn

Adam Przybyla

A rotating device for an at least partially opened gas turbine, is designed for being mounted on a parting line of the housing of the at least partially opened gas turbine by way of at least one connecting portion, wherein the rotating device has at least one first fastening portion, which is designed for mechanically interacting with a force-transmitting connection, in particular at least one traction cable, in order to pass on mechanically a rotating movement of at least one component of the at least partially opened gas turbine, wherein it has at least one sleeve, which has at least one second fastening portion, wherein the sleeve is designed for being connected non-positively to the gas turbine rotor.

Rotating device for a gas turbine and method for rotating a component

A securing device for securing a rotor of a turbomachine against tilting is provided, the rotor being arranged perpendicular in relation to a horizontal plane. The securing device includes a support surface enabling the rotor to be laterally supported in relation to the securing device. The rotor or the tie rod, arranged in an essentially vertical manner, are oriented vertically such that during an alignment, the support surface on which the rotor or the tie rod support, are displaced such that rotor is perpendicular in relation to the horizontal plane.

Securing device for securing a turbomachine rotor set up transversely to a horizontal plane against tipping over and orientation method therefor

A device for pivoting a rotor of a turbomachine from a first&#x2014;preferably horizontal&#x2014;position into a second&#x2014;preferably vertical&#x2014;position is provided. The rotor includes a plurality of rotor discs held together by at least one tension rod, the device includes two sidewall elements arranged parallel to one another, a bridge element connecting the sidewall elements to one another, and a divisible turning ring for form-fittingly holding an axial section of the rotor to be positioned perpendicularly. The rotor further includes two pins rotatably seated in the sidewall elements and arranged flush to the turning ring in order to pivot the turning ring about a pivot axis parallel to the horizontal plane. The bridge element includes a disk, wherein the disk is movable perpendicularly to the horizontal plane in order to be bolted in a flange-like manner onto a rotor retained by the device.

Device for pivoting a rotor of a turbomachine from a first position into a second position

An assembly device for assembling and disassembling a rotor of a turbomachine with rotor disks that are clamped together by at least one tie rod is provided. The assembly device includes a turning block that is secured to a base and a securing device that secures the rotor against tilting. The rotor is arranged in a transversal manner in relation to a horizontal plane of the base and pivotably mounted on the turning block. The securing device is fixed to the base by several supports and the turning block is arranged inside the surface of the base that is clamped by the supports. Large forces and torque coming from the rotor that is arranged in a perpendicular manner are guided from the securing device to the base.

Assembly apparatus for assembling and dismantling a turbomachine rotor composed of rotor disks

An arrangement is presented for axially securing rotating blades in a rotor, having a shaft collar on whose external circumference rotating blade securing grooves which extend in the axial direction of the rotor are provided. At one end side face of the shaft a projection is arranged in the region of the securing grooves, in which projection a circumferential groove which is open radially towards the outside is provided and said projection having securing grooves which are arranged in each rotating bade, sheet-metal-shaped sealing elements which each engage in the circumferential groove and in the securing groove and form an end side sealing ring in the circumferential direction being provided for axially securing the rotating blades, and at least one of the sealing elements comprising a sheet metal strip which is attached to said sealing ring in order to secure the sealing elements against displacement in the circumferential direction.

Arrangement for axially securing rotating blades in a rotor, sealing element for such an arrangement, and use of such an arrangement

The invention relates to a fitting device for producing the arrangement for locking a sealing element, arranged at the front end on a rotor of a turbine, against a displacement in the circumferential direction, the sealing element locking moving blades arranged on the rotor against an axial displacement. Furthermore, the invention comprises a method of producing the arrangement for locking a sealing element, arranged at the front end on a rotor of a turbine, against a displacement in the circumferential direction. The quality of the fitting can be further increased by means of a modular, mobile fitting device which secures the sealing element for the duration of the bending operation.

Fitting device for producing the arrangement for locking a sealing element, arranged at the front end on a rotor of a turbine, against a displacement in the circumferential direction, and method of producing such a locking arrangement

The invention relates to a method for cooling a gas turbine comprising a rotor, said method being carried out after the operation of the gas turbine and whereby the rotor is driven at least intermittently during a cooling phase at a reduced nominal speed. To provide a gas turbine with a reduced down time, a liquid is introduced at least intermittently into the air stream upstream of the compressor during the cooling phase.

Liquid injection in a gas turbine during a cooling down phase

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Langenfeld, Germany

Armin Hülfenhaus