Siemens Aktiengesellschaft

Arnd Reichert

Axel Buschmann

Markus Kunze

Dirk Lieser

Peter Tiemann

Mirko Milazar

Tobias Buchal

Volker Vosberg

Dieter Minninger

Harald Nimptsch

Heinrich Pütz

Bernd Stöcker

Kang Qian

Michael Neubauer

Gerhard Hülsemann

Micheal Strassberger

A fastening arrangement of a pipe is provided. The fastening arrangement is coaxial to a longitudinal axis, on a shaft step, which is rotatably mounted around the longitudinal axis, for connecting of the two component parts, with a coaxial circumferential surface located on the shaft step, upon which circumferential surface at least partially lies the inner side of the pipe end which faces the shaft step. In order to disclose the creation of a fastening arrangement which is especially simple and inexpensive to manufacture and also free of wear during operation, it is proposed that the pipe end has notches distributed over the circumference, and an encompassing annular slot on the inner side of the pipe in the region of the notches, with a sleeve which is installed in the annular slot, covers the notches, and at least partially lies on the circumferential surface of the shaft step.

Fastening arrangement of a pipe on a circumferential surface

The invention relates to a fastening arrangement of a pipe, which is coaxial to a longitudinal axis, on a shaft step, which is rotatably mounted around the longitudinal axis, for connecting of the two component parts, with a coaxial circumferential surface located on the shaft step, upon which circumferential surface at least partially lies the inner side of the pipe end which faces the shaft step. In order to disclose the creation of a fastening arrangement which is especially simple and inexpensive to manufacture and also free of wear during operation, it is proposed that the pipe end has notches distributed over the circumference, and an encompassing annular slot on the inner side of the pipe in the region of the notches, with a sleeve which is installed in the annular slot, covers the notches, and at least partially lies on the circumferential surface of the shaft step.

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 compressor, which is axially flowed through, for a gas turbine having an axially displaceable rotor. An annular flow channel, which narrows in an axial direction, is formed between a rotationally fixed outer delimiting surface and an inner delimiting surface on the rotor. A stationary ring comprised of guide profiles and at least one ring comprised of moving profiles attached to the rotor are placed inside said annular flow channel. The end of each moving or guide blade is located opposite an axial section of one of both delimiting surfaces while forming a radial gap. The aim of the invention is to provide a non-positive-displacement machine having an axially displaceable rotor whose velocity losses are at least not increased during an axial displacement of the rotor. To this end, the invention provides that the size of the radial gap between the end of each moving or guide blade and the opposite axial section of the delimiting surface is constant at least over the path of displacement of the rotor, and the radial gap extends parallel to the rotation axis of the rotor.

Turbomachine having an axially displaceable rotor

The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposing second surfaces. The seal element comprises a support structure and a sealing structure covering at least partially said support structure. The support structure comprises at least two contacting members, each contacting member serves for putting a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation of said surface. The invention further pertains to a combustion turbine, wherein a gap is formed between a first surface and a second surface, which gap is sealed off by said seal element.

Seal element for sealing a gap and combustion turbine having a seal element

An apparatus for controlling a cooling air flow, in particular a gas turbine cooling air flow, is for the control, specific to requirement, of a cooling air flow using low-maintenance. A control fluid flow is introduced into the cooling air flow in the region of the flow duct with a flow component transverse to the flow direction of the cooling air flow through the flow duct. As such, the flow rate of the cooling air flow is adjustable as a function of control parameters of the control fluid flow and/or other parameters.

Device and method for controlling a cooling air flow of a gas turbine

The invention relates to a turbo-machine ( ) comprising a rotor ( ) that extends along a rotational axis ( ). Said rotor ( ) has a peripheral surface ( ) which is defined by the outer radial delimitation surface of the rotor ( ) and has a receiving structure ( ) as well as a first moving blade ( A) and a second moving blade ( B). Each moving blade comprises a blade footing ( A, B) and a blade platform ( A, B). The blade platform ( A) of the first moving blade ( A) and the blade platform ( B) of the second moving blade ( B) border one another, and a gap ( ) is formed between the blade platforms ( A, B) and the peripheral surface ( ). A sealing system ( ) is provided in the gap ( ) on the peripheral surface ( ).

Turbo-machine comprising a sealing system for a rotor

The invention relates to a gas turbine ( ) having a turbine stage ( ) which has a guide blade ( ) and a feed ( ) for cooling air (K) with a cooling-air outlet ( ). The turbine stage ( ) can be cooled by the cooling air (K), the cooling-air feed ( ) having means via which a predeterminable pressure of the cooling air (K) can be set at the cooling-air outlet ( ).

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Duisburg, Germany

Arnd Reichert