Siemens Aktiengesellschaft

Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Tobias Buchal

Volker Vosberg

Georg Bostanjoglo

Ralf Müsgen

Matthias Oechsner

Thorsten Mattheis

Dirk Goldschmidt

Rudolf Küperkoch

Winfried Eβer

Ching-Pang Lee

Alexander Ralph Beeck

Peter Schröder

Fathi Ahmad

Jan Münzer

Ursula Pickert

Mirko Milazar

Andreas Böttcher

Bernd Prade

Gm Salam Azad

Vyacheslav Veitsman

Oliver Schneider

Sascha Dungs

Winfried Esser

Dieter Minninger

Michael Huth

Arnd Reichert

Francois Benkler

John Carl Glessner

Uwe Paul

Nicolas Savilius

Joachim Krützfeldt

Farzad Taremi

Uwe Kahlstorf

Björn Buchholz

Birgit Grüger

Torsten Koch

Katharina Bergander

Harald Nimptsch

Michael Neubauer

Anthony J Malandra

Andrew Lohaus

Martin Hartmann

Heinrich Pütz

Christian Nikasch

Oliver Lüsebrink

Rostislav Teteruk

Uwe Gruschka

Carmen Andrew Scribner

Kang Qian

Sven Bethke

Axel Schaberg

Thomas Hille

Martin Wilke

Kai-Uwe Rogos

Horia Flitan

Gerhard Hülsemann

Marc Bröker

Anna Kapustina

Eric Schwerin

Patricia Hülsmeier

Ekkehard Maldfeld

Gregor Frank

Elke Henschel

Alexander Schaufler

Olivier Gand

Waldemar Socha

Andreas BÖTTCHER

Hans-Jürgen Kiesow

Thorsten Koch

Simon Kliesch

A blade airfoil for an internally cooled turbine rotor blade has suction-side and pressure-side side walls, which, extending from a common leading edge to a common trailing edge and in a span direction from a root-side end to a tip-side end, at least partially enclose a cavity. The tip-side end includes a tip wall which delimits the cavity at the tip side. At least one cooling hole for the discharge of cooling fluid that can be caused to flow in the interior is provided. In the cavity, at least one rib which extends from the tip wall in the direction of the root-side end projects from the inner surface, surrounding the rib, of the suction-side side wall and/or from the inner surface of the pressure-side side wall. An inflow-side end, in relation to the cooling fluid, of the at least one cooling hole opens out laterally in the respective rib.

Blade airfoil for an internally cooled turbine rotor blade, and method for producing the same

A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, &#x3b1;, and exit angles, &#x3b2;. Airfoil inlet and exit angles are substantially in accordance with inlet angle values, &#x3b1;, and exit angle values, &#x3b2;, set forth in one of Tables 1, 2, 3, and 4.

Turbine airfoil with optimized airfoil element angles

An exhaust gas diffuser for a gas turbine is provided. The diffuser has an annular outer wall for guiding the diffuser flow and in which an annular guiding element is arranged concentrically to the outer wall and influences the diffuser flow. The guiding element has a surface which is radially directed inwards and has a circumferential contour that is convex in the longitudinal section to form a displacement element. The guiding element is axially displaceable between two positions so that the guiding element, when in a first position, allows a flow between the guiding element and outer wall and, when in a second position, largely prohibits a flow between the guiding element and outer wall. The aerodynamic effect of the diffuser is improved and simultaneously optimal adapted for a plurality of operational gas turbine states.

Exhaust gas diffuser for a gas turbine and a method for operating a gas turbine that comprises such an exhaust gas diffuser

A method for measuring and adjusting gaps between a rotor and a stator of a machine using a sensor is provided. The measuring is conducted when the rotor is operated at a rotational speed below a nominal rotational speed of the machine and without the machine being in operation. The adjusting of the gap is carried out as a function of at least one gap dimension of the gap. The sensor is not resistant to an operating temperature of the machine occurring in a region where the sensor is located. After completion of the measuring the machine is operated with the sensor.

Method for adjusting the radial gaps which exist between blade airfoil tips or rotor blades and a passage wall

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

The invention relates to a high temperature-resistant sealing assembly comprising a sealing segment and a component border which is connected to the sealing segment. A flexible sealing element is provided in order to joining the sealing segment and the component border. The invention is characterized in that the flexible sealing element compensates both thermal expansions and relative movements of the component border and the components resting against the sealing segment. The flexible sealing element and the sealing segment are subject to little wear and have a long service life. The invention further relates to a combustion chamber that is equipped with a high temperature-resistant sealing assembly as well as a gas turbine encompassing such a combustion chamber.

High temperature-resistant sealing assembly, especially for gas turbines

A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Gas turbine with a guide vane

The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Stator blade segment of a thermal turbomachine, associated production method and also thermal turbomachine

A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.

Turbine blade for a turbine with a cooling medium passage

A turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements is provided. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by a high-temperature and high-pressure bonding process. In the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.

Turbine blade

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

A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.

Combustion chamber for a gas turbine with at least two resonator devices

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Düsseldorf, Germany

Tobias Buchal