Alstom Technology Limited

Asea Brown Boveri Ag

Abb Alstom Power (switzerland) Ltd.

Alstom

Alstom (switzerland) Ltd

Gordon David Anderson

Bernhard Weigand

Fathi Tarada

Reinhard Fried

Shailendra Naik

Kenneth Hall

Stefan Schlechtriem

Michael Hock

Alexander Beeck

John Fernihough

Peter Marx

Thomas Zierer

Markus Oehl

Joerg Stengele

Marcel Koenig

J&ouml;rgen Ferber

Joergen Ferber

Volkmar J Galke

Michael Loetzerich

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

For preparing a gas stream cleaned from dust and dirt particles, a device is proposed in which an outflow channel () for cleaned medium has at its mouth in an inflow channel () an extension element (), which projects into the inflow channel. A cover element () covers an end inflow aperture () of the extension element. In an embodiment of the invention, the extension element () has lateral inlet apertures (). The cover element () is preferably constituted hood-shaped, and has axial extension elements (), which at least partially cover the extension element () in the axial direction, and advantageously extend over the lateral inlet apertures. The stream entering the outflow channel () for cleaned medium must overcome strong flow deflections, so that particles with a low flow following ability cannot get into this channel. Further outflow channels () for conducting the remaining dust-laden medium are arranged substantially flush with the wall () of the inflow channel.

Device for filtering particles out of a coolant flow in a turbo machine

Device for separating dirt and debris in flowing media

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

The invention relates to an impact flow for wall sections including a plurality of impact openings which are arranged on a plane in a flat or curved support. The support is fitted it a distance from the wall section, and the impact surface of the wall section that is to be cooled is configured as a bulged relief. The bulge elements are arranged around the impact surface of the impact beam. The surfaces of the bulge elements facing the impact beam include two curves which blend into one another.

Turbine blade wall section cooled by an impact flow

The invention relates to a method for producing a cooled cast part for a thermal turbo machine by using a known casting process. Between a wax model of the cast part and a ceramic core, a wax seal is applied by hand above a step, only on an additional shoulder. The material that is created during the casting process at this point by the shoulder and the wax seal can be ground off without causing rough areas on the step to form. This simplifies the welding or soldering of a cooling plate to the step.

Method for producing a cooled, lost-wax cast part

A hot-gas stream (,) flows along the surface of a segment arrangement for shroud bands, in particular in a gas turbine. The segment arrangement comprises segments (,&prime;) arranged next to one another and in each case separated from one another by a gap (,). The hot-gas stream (,), in at least one section (,) of the gap (,), has a velocity component perpendicular to the direction of the gap from a first segment (,) to a second segment (,&prime;). In this case, in said section (,), along that edge (,) of the first segment (,) which faces the gap (,), at least one film-cooling bore (,) connects a cooling-air chamber (,), allocated to the first segment, to the surface (,) subjected to the hot-gas stream (,), and/or, in said section (,), along that edge (,&prime;) of the second segment (,&prime;) which faces the gap (,), at least one edge-cooling bore (,) connects a cooling-air chamber (,&prime;), allocated to the second segment, to the inside (,&prime;) of the gap (,).

Cooling arrangement for gas-turbine components

A method of applying a surface coating to a stator vane (1) of a gas turbine, the stator vane (1) comprising a platform (3) with an outer surface (4) connected to the stator of the gas turbine and an airfoil (2) connected to the platform (3), the method comprising the steps of each stator vane (1) is provided as a singlet, a base layer coating (7) affording resistance to oxidation is applied to surfaces of said stator vane (1) and said outer surface (4) of the platform (3) to be exposed to hot gases of the gas turbine, and a top layer coating (8) affording thermal resistance is applied to all coated surfaces of said stator vane (1) and the outer surface (4) of the platform (3), and welding the stator vanes (1) together, wherein a welding filler material (10) is placed between said walls of two adjacent platforms (3) of said stator vane (1), welding said singlets to one another at the margins of walls of said platform (3) to said welding filler material (10).

Method for coating and welding stator vanes of a gas turbine

Platform cooling having a guide-blade platform (30; 60) which is subjected to a hot-gas stream (20) and is separated by a gap (36; 66) from a combustion-chamber segment (40; 70) arranged upstream, one or more segment cooling bores (42; 72) being made in the combustion-chamber segment (40; 70), which segment cooling bores (42; 72) connect a cooling-air chamber (44; 74) to the gap (36; 66). The guide-blade platform (30; 60) has a surface (34; 64) on the downstream side in the region of the gap (36; 66), the axes of the one or more segment cooling bores (42; 72) running roughly tangentially to said surface (34; 64).

Platform cooling for gas turbines

The invention relates to a device for operating an annular combustion chamber (15) which is equipped with combined burners (1) for liquid (4) and gaseous fuels (9), in particular burners of the double-cone design, each burner (1) having a fuel lance (3), with at least one additional air passage (7), for feeding the liquid fuel (4) and an airblast nozzle (2) for atomizing the liquid fuel (4), into which airblast nozzle (2) atomizing air (5) is fed from outside the burner hood (13), and an adjusting mechanism being provided for at least partly throttling the inflow of the atomizing air (5) during gas operation, wherein the adjusting mechanism is an external valve (21) which is arranged in a main feed line (19), coming from the compressor outlet (18), for the atomizing air (5), the main feed line (19) leading into a ring line (20), and the ring line (20) being connected to the head (24) of each fuel lance (3) via one branch line (23) each.

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Baden, Switzerland

Gordon David Anderson