Alstom (switzerland) Ltd

Asea Brown Boveri Ag

Alstom

Abb Research Ltd.

Alstom Power N.v.

Abb Alstom Power (schweiz) Ag

Abb Alstom Power (switzerland) Ltd.

Alstom Technology Limited

Alexander Beeck

Bernhard Weigand

Beat Von Arx

Mohamed Youssef Nazmy

John Fernihough

Ibrahim El-Nashar

Ulrich Rathmann

Christoph Nagler

Erhard Kreis

Klaus Semmler

Peter Ernst

J&ouml;rgen Ferber

Konrad Vogeler

Lothar Schneider

Bernhard Bonhoff

Hans Wettstein

Reinhard Fried

Herbert Brandl

Jakob Keller

Shailendra Naik

Andreas Boegli

Hartmut Haehnle

Gordon David Anderson

Wilhelm Endres

Markus Oehl

Joerg Stengele

Bruce Johnson

Sacha Parneix

Andreas B&ouml;gli

Pey-Shey Wu

G&uuml;nter Wilfert

Klaus Erich Schneider

Mark Richter

Christoph Tonnes

Cornelis Striezenou

Hans-Joachim Roesler

Christoph Töennes

A honeycomb structure is arranged on a stator of a gas turbine and is arranged opposite the moving blades of the gas turbine. The honeycomb structure is composed of metal sheets in such a way that webs having double the sheet thickness are obtained and connections of single thickness are obtained between the webs. The angle &agr; between the circumferential direction of the stator and the webs of double thickness is 5&deg; to 175&deg;. This serves to avoid undesirable efforts such as, for example, overheating during friction at the honeycomb structure of the moving blades of the gas turbine.

Sealing of a thermal turbomachine

A platelike projecting component portion of a component used in gas turbines or other similar applications includes a surface upon which hot gas acts and cooling bores through which a cooling medium is capable of flowing. Effective cooling is achieved by providing at least one plenum assigned solely to the component portion. The plenum is arranged so as to be directly adjacent to the surface upon which hot gas acts and through which the cooling medium is capable of flowing to provide convective heat transfer. The cooling bores are designed as blow-out orifices which emanate from the plenum and issue the cooling medium onto the surface upon which hot gas acts, thereby forming a cooling film.

Platelike projecting component portion of a gas turbine

A nondestructive method for determining the thickness of a metallic protective layer determined by detection of a different type of intervening layer which is situated between the metallic protective layer and the metallic base material, by ultrasound, eddy-current or (pulsed) thermography. The intervening layer may comprise a nonmetallic layer of oxides or carbides, a metallic layer of pure nickel or a layer with depleted Al and Ti content in that region of the base material which is close to the surface. This method can be used for turbine blades in order to determine the layer thickness, for example during the test phase of coating, and to avoid the known destruction of the turbine blade, which is labor- and cost-intensive.

NONDESTRUCTIVE METHOD FOR DETERMINING THE THICKNESS OF A METALLIC PROTECTIVE LAYER ON A METALLIC BASE MATERIAL VIA A DIFFERENT TYPE OF LAYER BETWEEN THE METALLIC PROTECTIVE LAYER AND THE METALLIC BASE MATERIAL

In a hollow-cast component, a core opening ( ) created during manufacturing is closed with a closure piece ( ). This closure piece is located inside a recess ( ) in the component, whereby the recess is arranged so that it is imbedded completely in the cast material, and completely covers the core opening. Because of this installation, the closure piece is fixed in a form-fitting manner in the direction of two spatial axes, so that the closure piece only needs to be secured with an additional joint in the installation direction. It is preferred that the installation direction is normal in relation to the direction of maximal stress of the closure piece, so that a joint is subject to a relatively small stress and therefore can be produced with little expenditure and a high degree of operational safety.

Hollow-cast component

A component such as a turbine blade ( ) of a gas turbine is provided with an intermetallic felt ( ). By providing the tip ( ) of the turbine blade ( ) with the intermetallic felt ( ) and optionally a coating of a ceramic material ( ), improved protection against thermal and mechanical effects and improved oxidation resistance can be achieved. Also conceivable would be an arrangement of the intermetallic felt ( ) at the rotor ( ) or stator ( ) opposite from the turbine blade ( ) or on the platform ( ) of the turbine blade ( ).

Friction-susceptible component of a thermal turbo machine

A heat shield of a turbo machine is provided with a microstructure. In a preferred embodiment, the microstructure element comprises a plateau, which is arranged on a rib in such a way that the structure has a &ldquo;T&rdquo;-shaped cross section. The ribs are preferably embodied as plates set on edge on the heat shield and are aligned with their surface perpendicular to the circumferential direction (U) of the turbo machine. This results in low bending dimensional rigidity in the circumferential direction. In this way, it is possible to accommodate scraping of a component involved in relative motion in the circumferential direction without plastic deformation. Moreover this arrangement gives the maximum possible resistance to a leakage flow. When used at high temperatures, it is furthermore advantageous to provide ways to enable a coolant to be supplied to the microstructure.

Turbo machine

In a gas-turbine guide element ( ) around which a hot air flow ( ) flows and which, at least in a trailing edge region ( ), in which the air flow ( ) separates from the guide element ( ), comprises at least two walls ( ) arranged essentially in parallel and connected to one another by ribs ( ) in such a way as to form internal cooling passages ( ), and which is cooled on the inside with cooling medium ( ) flowing through the cooling passages ( ), the cooling medium discharging from the guide element ( ) at the trailing edge ( ) essentially parallel to and between the walls ( ), and in a method of producing it, easier reworking and less susceptibility to foreign particles are achieved owing to the fact that at least some of the ribs are arranged as choke ribs ( ) so as to terminate essentially flush with the trailing edge ( ).

Blade for gas turbines with choke cross section at the trailing edge

Arrangement for cooling a flow-passage wall surrrounding a flow passage, having at least one rib element

A cooling arrangement for blades of a gas turbine or the like, in each case the blades being built up from a suction-side wall and a pressure-side wall which are connected, to form a cavity, via a leading edge, a trailing edge, a blade tip and a blade root, and a flow path, through which a cooling medium, in particular steam, is capable of flowing, being integrated in the cavity, and in which the flow paths in each case of two or more adjacent blades are connected to one another in such a way that a continuous cooling duct sealed off relative to the hot-gas stream is formed. It thus becomes possible to increase cooling efficiency by better utilization of the cooling medium and at the same time to reduce the outlay in terms of construction.

Cooling arrangement for blades of a gas turbine

A rotor for a gas turbine comprises a multiplicity of rotor blades of which each comprises a blade airfoil, a blade root and a platform arranged between blade airfoil and blade root and each of which, together with the blade root, is pushed into an axial location slot, which is arranged on the outer periphery of a rotor disk, and is releasably retained there in such a way that hollow spaces are formed between the platform and the peripheral surface of the rotor disk, and each of which is supplied, for cooling purposes, with cooling air through at least one cooling air supply passage extending in the rotor disk and emerging into the location slot, which cooling air is fed through the blade root to within the blade airfoil.

Rotor for a gas turbine

A thermally highly loaded casting is produced. The casting mold is produced from a slurry using a wax model and a polymer foam which is fixed to the wax model or has been introduced into a cavity. In this way, during the casting process the liquid superalloy also penetrates into the open-cell structure of the casting mold, so that an integral cooling structure is formed during the solidification of the casting. A single-crystal or directionally solidified casting is advantageously produced. It is also conceivable to vary the cell size of the polymer foam, to produce a cooling structure and a base material separately, and to coat the cooling structure with a ceramic protective layer (thermal barrier coating).

Process for producing a thermally loaded casting

A cooling passage of a component subjected to high thermal loading, which is formed as a cavity ( ), running in a longitudinal direction (L) and curved orthogonally to the longitudinal direction (L), between a first wall ( ) and a second wall ( ), which in each case are connected to one another in a laterally adjacent manner, which has ribs ( ), which are arranged on the first wall ( ) and the second wall ( ) such that they alternate in a longitudinal direction (L) and are staggered relative one another and, at least in sections, assume a non-orthogonal angle relative to a projected center axis ( &prime;), and through which a cooling fluid (K) can flow in a longitudinal direction (L), in which case, when the profile of the cavity ( ) is curved orthogonally to the longitudinal direction (L), the ribs ( ) are formed in such a way that, in each case locally with regard to the adjacent rib of the opposite wall, they maintain a distance (a) which is half a respective local rib spacing (p). It is thereby possible to even out the heat transfer at a curved passage profile.

Cooling passage of a component subjected to high thermal loading

In an air-cooled turbine blade which, at the blade tip, has a shroud-band element extending transversely to the longitudinal axis of the blade, a plurality of cooling bores passing through the shroud-band element for the purpose of cooling, which cooling bores are connected on the inlet side to at least one cooling-air passage running through the turbine blade to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade, improved and assured cooling is achieved owing to the fact that the cooling bores run from inside to outside in the shroud-band element at least approximately parallel to the direction of movement of the blade and in each case open upstream of the outer margin of the shroud-band element into a surface recess open toward the exterior space. The top side of the shroud band is preferable provided with at least two ribs and, which run in parallel and, in interaction with the opposite casing wall, form a cavity, into which the cooling air discharging from the cooling bores flows.

Turbine blade with actively cooled shroud-band element

A method is disclosed for preventing harm caused by constrictions in the cooling holes of gas-cooled parts, in particular of gas turbines and/or burners. These constrictions form because the walls of the gas-cooled parts through which the cooling holes extend and which are covered on their outside with a protective, first coating are provided during the course of an overhaul with a second, repeat coating, and coating material is deposited in the cooling holes. Constant flow ratios in the cooling holes are achieved in a simple manner in that prior to the overhaul, the cooling holes are constricted with first means to an extent that corresponds to the later constrictions created during the course of the second coating. The first means are removed after the overhaul. The first means takes the form of an insert with holes that constrict the flow through the cooling holes.

Method for preventing harm from constrictions formed during coating with a protective coat in the cooling holes of gas-cooled parts

Described is a sealing arrangement for reducing leakage flows inside a rotary fluid-flow machine, preferably an axial turbomachine, having moving and guide blades, which are in each case arranged in at least one moving- or guide-blade row respectively and have blade roots, via which the individual moving and guide blades are connected to fastening contours. A sealing element having felt-like material is provided between at least two adjacent blade roots within a guide- or moving-blade row or between guide and/or moving blades and adjacent components of the fluid-flow machine.

Sealing arrangement

Growing community of inventors

Küssaberg, Germany

Alexander Beeck