Siemens Aktiengesellschaft

Dieter Minninger

Peter Schröder

Andreas Böttcher

Vyacheslav Veitsman

Tobias Buchal

Volker Vosberg

Francois Benkler

Uwe Kahlstorf

Bernd Stöcker

Michael Neubauer

Stephan Schmidt

Steffen Skreba

Mirko Milazar

Matthias Heue

Oliver Schneider

Arnd Reichert

Harald Nimptsch

Stefan Dahlke

Uwe Sieber

Heinrich Pütz

Martin Hartmann

Kang Qian

Uwe Gruschka

Andreas Peters

Ulrich Beul

Rostislav Teteruk

Martin Lenze

Torsten Matthias

Bernhard Küsters

Hajrudin Ceric

Gerhard Hülsemann

Axel Schaberg

Marc Mittelbach

Stefan Völker

Roger Waldinger

Boris Dobrzynski

Holger Bauer

Patricia Hülsmeier

Thomas Matern

Ekkehard Maldfeld

Ralf Hoffacker

Andreas Stiehm

Adam Zimmermann

Andreas BÖTTCHER

Tilman Auf Dem Kampe

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

Disclosed is a gas turbine for a thermal power plant, especially a gas turbine, comprising a rotatable rotor and a duct which can be penetrated by a gas and in which turbine blades for driving the rotor are disposed. The inventive gas turbine is characterized by a blocking device which at least partially prevents the gas from penetrating the duct in a closed position.

Gas turbine for a thermal power plant, and method for operating such a gas turbine

A gas turbine, comprising a turbine and a compressor provided with a compressor housing, and to a method for the operation thereof. The compressor is tapped in order to cool the turbine by means of at least one tap line for removing compressed or partially compressed air. The tap line comprises a locking device, particularly a valve, in order to regulate the outflow of tapped air and thus the cooling of the housing.

Gas turbine with a compressor housing which is protected against cooling down and method for operating a gas turbine

The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in turbo-machine. The aim of invention is to develop a device and a method for the turbo-machine making it possible to reduce the size of a radial split of the turbo-machine in order to obtain greater degree of efficiency. The inventive turbo-machine comprises a rotor rotationally mounted in the case of the turbo-machine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and arrangement influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbo-machine rotor by heating fluid flowing there-through are also disclosed.

Turbomachine, in particular a gas turbine

The invention relates a method for improving the hot-starting behavior of a turbomachine. By virtue of the setting of a radial gap formed between a brushing edge of a blade profile and a guide face lying opposite this, in which setting a guide ring forming the guide face can be acted upon with a coolant, the hot-starting behavior can be improved, in that the guide ring is cooled before the start of the machine.

Method for setting a radial gap of an axial-throughflow turbomachine and compressor

The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The aim of said invention is to develop a device and a method for the turbo-machine making it possible to reduce the size of a radial split of the turbo-machine in order to obtain greater degree of efficiency. The inventive turbo-machine comprises a rotor rotationally mounted in the case of the turbo-machine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and an actuating device dependent on centrifugal force is provided.

Growing community of inventors

Dinslaken, Germany

Dieter Minninger