Siemens Aktiengesellschaft

Francois Benkler

Harald Hoell

Peter Schröder

Vyacheslav Veitsman

Oliver Schneider

Walter Loch

Andreas Böttcher

Karsten Kolk

Mirko Milazar

Peter-Andreas Schneider

Tobias Buchal

Sascha Dungs

Olga Deiss

Thomas Grieb

Daniel Grundei

Ulrich Ehehalt

Uwe Kahlstorf

Dieter Minninger

Rudolf Küperkoch

Nicolas Savilius

Harald Nimptsch

Vadim Shevchenko

Guido Ahaus

Martin Hartmann

Rostislav Teteruk

Shilun Sheng

Dirk Wistuba

Torsten Matthias

Uwe Lohse

Marc Mittelbach

Michael Neubauer

Frank Deister

Stephan Klumpp

Karl Klein

Jörn Bettentrup

Ekkehard Maldfeld

Patricia Hülsmeier

Achim Schirrmacher

Thomas Brandenburg

Horst Saathoff

Marion Morthorst

Michael Rollmann

Andreas BÖTTCHER

An axial compressor for compressing a flow medium is provided and includes compressor stator blades, which fastened on a stator blade carrier, and compressor rotor blades, which are fastened on a compressor disk of a compressor shaft, wherein two consecutive compressor disks enclose a hollow space lying between them, and wherein the last compressor disk, as seen in the flow direction of the flow medium, delimits a rear hollow space. A cooling medium feed duct leads through a stator blade carrier and a compressor stator blade, and is arranged upstream of the last compressor disk, which cooling medium feed duct, at the tip end of the compressor stator blade facing the compressor shaft, via a discharge opening arranged there, opens into the hollow space, wherein this hollow space, via a cooling medium transfer passage which is led through the subsequent compressor disks, is connected to the rear hollow space.

Axial compressor and associated operating method

A gas turbine including a plurality of hook elements disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and including a stator blade support, is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the hook elements or the stator blade support has a substantially elliptical cross-sectional contour.

Gas turbine

An axial turbomachine including a rotor-blade cascade is provided. The turbomachine includes a casing in which the cascade is installed and a guide-blade carrier which encloses the cascade and is integrated into the inner side of the housing. The guide-blade carrier is arranged immediately adjacently to the blade tips faulting a radial gap, wherein the guide-blade carrier is mounted in the housing, such that it may be displaced parallel to the axis of the axial turbomachine, and includes an adjusting ring which is supported on contact surfaces on the housing and guide-blade carrier and may be rotated about the axis, wherein the contact surfaces of the adjusting ring and of the housing and/or of the guide-blade carrier are set with respect to a plane perpendicular to the axis, so that, when the adjusting ring is rotated about the axis, the guide-blade carrier is displaced axially by the adjusting ring.

Axial turbomachine having an axially displaceable guide-blade carrier

A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Rotor of a gas turbine

A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Rotor for a gas turbine

A turbomachine rotor, a rotor blade and a method for assembling a turbomachine rotor are provided. The turbomachine rotor includes a rotor blade with a blade root, a wheel disk with a groove in which the blade root engages such that the rotor blade is maintained in the groove in a positive fit in a radial direction. Further, a pretensioning device is provided, which is supported on the wheel disk as well as on the blade root and which exerts a pretensioning force on the blade root in the radial direction. The pretensioning device is designed such that the pretensioning force can be adjusted when assembling the turbomachine rotor.

Turbomachine rotor comprising a pretensioning device for pretensioning a rotor blade

A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.

Turbine with at least one rotor which comprises rotor disks and a tie-bolt

Growing community of inventors

Ratingen, Germany

Francois Benkler