Siemens Aktiengesellschaft

Siemens Energy, Inc.

Stefan Irmisch

Alexander Ralph Beeck

Werner Stamm

Hans-Thomas Bolms

Eckart Schumann

Jan Münzer

Matthias Oechsner

Michael Dankert

Martin Feldhege

John P Dalton

Rex A Smith

Stuart Bishop

Tilmann Auf Dem Kampe

Frank A Maichle

There is described a method with which, on the basis of a three-dimensional recording of a component to be reworked, its surface configuration can be determined and stored temporarily so that, after it has been coated, it can be produced in its original surface form, or in its surface form then required, in certain regions, i.e. locally in the area of film-cooling openings. An especially precise and quick three-dimensional recording can be achieved by the use of the triangulation method. In this case, a reference pattern depicted on the component by a projector is recorded by two camera arranged at an angle. From the images from the cameras, the coordinates describing the surface three-dimensionally can then be determined by a control system using the triangulation method.

Method for producing a gas turbine component which is to be coated, with exposed holes, device for carrying out the method, and coatable turbine blade with film cooling holes

There is described a gas turbine with a channel wall that limits a flow, said channel wall comprising first and second wall sections, one of the wall sections being part of a combustion chamber of the gas turbine and the other wall section being part of an annular hot gas channel of a turbine unit, and the two adjacent wall sections facing each other with a gap there between. In order to reduce the leakage quantities of blocking gas that protect the gap from the entry of hot gas, it is proposed that blocking element projects from the side of the first wall section into the gap and can be displaced transversely thereto, said blocking element comprising a piston face disposed in the first wall section and a sealing structure lying opposite the piston face, it being possible to press said sealing means against an end sealing section of the second wall section by means of a pressure medium that acts on the piston face.

Gas turbine with a gap blocking device

Introducing a plurality of geometrically shaped members () into a cooling passage () of a gas turbine airfoil () will effectively reduce the cross-sectional flow area while simultaneously retaining a sufficiently thick external contour desired for proper gas path aerodynamic behavior. Small cooling sub-passages () formed around the geometric members will create a preferentially higher coolant flow rate and heat transfer coefficient at the cooled surface () when compared to the interior of the cavity. The geometric shapes may be metal or ceramic spheres retained in the cooling cavity by a retaining structure such as a screen grid () or perforated plate (). The openings () in the retaining structure may be unevenly distributed to preferentially allow more coolant to enter the cavity proximate the cooled walls. The size/shape of the geometrically shaped members may be varied to achieve a desired heat transfer coefficient along the cooled wall surface ().

Gas turbine component with reduced cooling air requirement

Method for recording microstructural changes in a layer system component. A specific material parameter of the component is measured. The layer system may include an alloy substrate and an alloy or porous ceramic layer. The material parameter may be measured a plurality of times. The measured material parameter may include electrical capacitance, specific heat capacity, peltier coefficient or magnetic susceptibility. The material parameter may first be measured on a new component and subsequent measurements may be performed at a time interval after operational use. The recorded material parameter is then used to determine microstructural changes in the substrate or the layer material of the component caused by changes in precipitation, cracks, or depletion of an alloying element.

Method for recording microstructural changes in a component

The invention relates to a turbine blade or vane for a gas turbine, having a blade or vane root, which is successively adjoined by a platform region with a transversely running platform and then a blade or vane profile which is curved in the longitudinal direction, having a platform surface, which is provided at the platform and can be exposed to hot gas, and having at least one cavity, which is open on the root side, through which a coolant can flow and which extends through the blade or vane root and at least into the platform region and is surrounded by an inner wall, the contour of which, running in the platform region, is set back with respect to the contour running in the blade or vane root, so as to form a recess. To provide a turbine blade or vane which has a service life which is extended with respect to fatigue while at the same time saving cooling air, the invention proposes that the recess, as a partial cavity, is set back so deep into the platform that it lies opposite the platform surface, forming an at least partially hollow platform, and that there is at least one means for diverting the coolant into the partial cavity.

Cooled turbine blade or vane for a gas turbine, and use of a turbine blade or vane of this type

The invention relates to a gas turbine blade or vane ring having a supporting structure and gas turbine blades or vanes secured to it. The gas turbine blades or vanes have a blade or vane root, which is successively adjoined by a platform and then a blade profile which is curved in the longitudinal direction, the blade or vane root running in the longitudinal direction of the blade profile, and the platform having two platform longitudinal edges which are bent parallel and run in the longitudinal direction. To provide an alternative gas turbine blade or vane ring with simplified assembly, it is proposed that the blade or vane root be shaped in such a manner that the suction-side or pressure-side blade or vane root surface of the associated platform longitudinal edge be curved convexly or concavely, respectively. Moreover, the invention relates to the use of a gas turbine blade or vane ring of this type.

Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring

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Niederrohrdorf, Switzerland

Stefan Irmisch