Siemens Aktiengesellschaft

Uwe Sieber

Markus Hofmann

Harald Hoell

Vyacheslav Veitsman

Andreas Heselhaus

Christian Cornelius

Sascha Dungs

Malte Blomeyer

Dieter Minninger

Ulrich Waltke

Nicolas Savilius

Michael Wagner

Marco Link

Patrick Ronald Flohr

Patrick Bullinger

Vadim Shevchenko

Guido Ahaus

Bernhard W Küsters

Dimitri Zelmer

Mario Koebe

Dirk Wistuba

Elliot Griffin

Torsten Matthias

Ulrich Beul

Frank Mildner

Stefan Völker

Hubertus Michael Wigger

Frank Woditschka

Daniel Gloss

Stephan Klumpp

Sebastian Stock

Marc Mittelbach

Marcel Eifel

Romain Bayere

Ralf Hoffacker

Achim Schirrmacher

Stefan Reichling

Markus Paus

Boris Dobrzynski

Ingo Balkowski

Andreas Stiehm

Adam Zimmermann

Oliver Ricken

Thomas Brandenburg

Waldemar Heckel

Christian Lyko

Bernward Mertens

Tilman Auf Dem Kampe

Daniel Ecke

Bernhard Küsters

A closing assembly for closing a blade ring inserted into a circumferential T-groove of a blade support of a turbomachine, having two insertion elements, each has a C-shaped basic form having a resting leg, retention leg, and connection leg connecting the resting leg and the retention leg and is designed to reach around a ridge of the T-groove. The resting leg reaches over the ridge and the retention leg reaches under the ridge, and an intermediate element, is positioned between the insertion elements to prevent the insertion elements from moving to the center of the T-groove. The intermediate element reaches below the retention legs of the insertion elements in the assembled state, and a positioning element is associated with the intermediate element, which is supported between the groove base of the T-groove and the intermediate element and to position the intermediate element at a desired distance from the groove base.

Closing assembly for closing a blade ring, associated blade supports, turbomachine, and method for inserting a closing assembly

A blade arrangement is provided having a blade carrier and a retaining groove arranged therein, which retaining groove has projections extending along side walls thereof forming undercuts and into which a number of blades are inserted forming a blade ring of a turbomachine. Each blade has a blade root which engages into the undercuts, and each blade is pressed against the projections by an element arranged between a blade root underside and a groove base of the retaining groove. It is further provided that each element is of plate-like form and has, in the projection of the blade airfoil in the direction of the groove base, at least one bead, arranged beneath the blade airfoil, for imparting a pressing action, and in the longitudinal direction of the retaining groove, only part of the blade root which the element presses against is covered.

Blade arrangement

An internally coolable component for a gas turbine with at least one cooling duct, on the inner surface of which swirl elements are arranged in the form of turbulators which extend transversely with respect to the main flow direction of a coolant is provided. In order to reduce pressure losses for the coolant in the cooling duct, pins with different heights are set up between the turbulators.

Internally coolable component for a gas turbine with at least one cooling duct

A stator blade and a stator blade arrangement for a turbomachine which is exposable to axial throughflow is provided. Each stator blade is retained via a fixed clamping in a circumferential groove. For the fixed clamping, provision is made on one side of the blade root for a shaped piece with a threaded hole into which a tensioning screw, which is supported on the bottom of the circumferential groove, may be screwed.

Stator blade for a turbomachine which is exposable to axial throughflow, and also stator blade arrangement for it

Disclosed is an annular flow duct for a turbomachine, the flow duct arranged concentrically about a machine axis running in the axial direction and defined by a boundary wall of circular cross section for directing a main flow, wherein the boundary wall has a plurality of return flow passages distributed over its circumference and through which in each case a partial flow is detached from the main flow at a bleed position and returned to the main flow at a feed position situated upstream of the bleed position, and having aerofoils, arranged radically in the flow duct, of a blade ring, the aerofoil tips of which lie opposite the boundary wall, with a gap formed in each case, wherein the aerofoils are movable in a predetermined rotation direction along the circumference of the boundary wall. Furthermore, a compressor which is insensitive to pumping and flow separations, as viewed in rotation direction, the bleed position of each return flow passage lies upstream of the corresponding feed position.

Annular flow duct for a turbomachine through which a main flow can flow in the axial direction

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Mülheim an der Ruhr, Germany

Uwe Sieber