Alstom Technology Limited

General Electric Technology Gmbh

Stefan Schlechtriem

Beat Von Arx

Reinhard Fried

Ulrich Rathmann

Gordon David Anderson

Sacha Parneix

Helene Saxer-Felici

Shailandra Naik

Shailendra Naik

Thomas Zierer

Markus Oehl

Peter Graf

Helmar Wunderle

Joerg Stengele

Silvio Glaser

Michael Loetzerich

A method is described for improving the sealing between rotor and a plurality of blades. The rotor has a plurality of generally axially extending profiled recesses into which a ring of blades, which have corresponding blade root profiles, are inserted in a form-fitting and/or frictionally locking manner into these recesses in a generally axial insertion direction. Between the recesses the rotor has tangential surface sections or circumferential surface sections which extend in the axial direction and circumferential direction and are generally indirectly covered by lower shrouds of circumferentially adjacently arranged blades in the radial direction. At least one of the tangential surface or circumferential surface sections is provided with a step in the radial direction, and a corresponding recess, which adjoins as flush as possible, is provided in the underside of the shroud of the blade which is arranged above it. Corresponding rotors or blades are also described.

Method for improving the sealing on rotor arrangements

A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct. An orifice can, for example, extend from the main coolant inlet to the second deflection region.

Cooled blade for a gas turbine

The invention describes a device for separating dust and dirt out of flowing media. A curved flow path () is imposed on the flow (), and heavy foreign bodies are separated out of the main flow by centrifugal force. The partial stream required to carry away the foreign bodies is aftertreated in a filter () and returned in purified form. Unlike with conventional filters, which have to process the entire flow of media, pressure losses during the separation of dust are minimized, and on the other hand no medium is lost for removing the dust load.

Device for separating dust and dirt out of flowing media

A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.

Cooled blade or vane for a gas turbine

The invention discloses a process for treating a ceramic protective layer ( ) which is applied to the surface ( ) of a gas turbine part ( ). The roughness of the ceramic protective layer ( ) is reduced at at least one first location ( ), and the original roughness is retained at at least one second location ( ). The roughness is advantageously retained at locations ( ) on a turbine blade or vane ( ) which are at risk of detachment, while the roughness of the remaining surface ( ) is reduced in order to reduce the heat transfer to the surrounding hot-gas flow.

Process for treating a coated gas turbine part, and coated gas turbine part

Growing community of inventors

Taegerig, Switzerland

Stefan Schlechtriem