Abstract: The invention relates to a high-temperature alloy for a mechanically highly stressed component of a thermal machine based on doped TiAl and a method to improve a mechanical property of the alloy. The alloy has the following composition (in atomic %): 44.5 to <46 Al, 1-4 W, 0.1-1.5 Si, 0.0001-4 B, and the rest Ti and contaminations due to the manufacturing process. The alloy is characterized by improved heat resistance and ductility at high temperatures, and at the same time good oxidation and corrosion resistance.

Abstract: A metallic component exposed to high temperature steam is provided with a coating comprising a thin primer layer deposited on the surface of the metallic component and a thicker overlay layer on top of the primer layer. The primer layer consists of highly ductile, oxidation resistant material such that it remains free of any defects over a long period of exposure. The overlay layer consists of an oxidation resistant, less ductile, and low-cost material. It protects the thin primer layer from mechanical damage and chemical degradation. The primer layer protects the base material of the metallic component from oxidizing steam that may penetrate through cracks of the overlay layer. Due to suitable choice of coating materials and thicknesses of the layers the coating is low-cost.

Abstract: A semi-modular rotor module for an air preheater having a circular rotor includes a lug assembly having a lug front, a lug back spaced radially outward from the lug front, and cold end and hot end lug members. The lug front and lug back each extend longitudinally from a first end to a second end, with the cold end lug member being mounted to the first ends of the lug front and the lug back and the hot end lug member being mounted to the second ends of the lug front and the lug back. A single main diaphragm extends radially from an inner end portion to an outer end portion, with the inner end portion being mounted to the lug front on a first side of the lug assembly. The outer end portion is mounted to a rotor shell which is spaced radially outward from the lug back. At least one intermediate diaphragm extends radially from an inner end portion, mounted to the lug back at a position intermediate the first and second sides of the lug assembly, to an outer end portion mounted to the rotor shell.

Abstract: In a method for the nondestructive quality testing of a thermocouple (10) which can be used in particular at high temperatures and/or under high levels of vibration, which thermocouple (10) comprises at least two wires (13, 14) which run substantially parallel to one another in one plane, are connected to one another at their ends by a welded joint (15), are surrounded by a hermetically sealed sheath (11) and inside the sheath (11) are embedded in insulation (16, 17) comprising a compacted powder, simple and reliable assessment is achieved by the fact that the X-radiation is passed through the thermocouple (10) perpendicular to the plane of the wires (13, 14) and an X-ray image is taken, that the position of the wires (13, 14) in the vicinity of the welded joint (15) is determined from the X-ray image, and that the quality of the thermocouple (10) is established from the position of the wires (13, 14) in the vicinity of the welded joint (15).

Abstract: An arrangement for cooling a flow-passage wall surrounding a flow passage is described, having at least one rib feature which induces flow vortices in a flow medium passing through the flow passage, is attached to that side of the flow-passage wall which faces the flow passage, and has a main longitudinal extent which is oriented at an angle of &agr;≠0° to the direction of flow of the flow medium passing through the flow passage. The invention is characterized in that the rib feature, along the main longitudinal extent, at least partly has rib-feature sections whose axes enclose an angle of &bgr;≠0° with the main longitudinal extent.

Abstract: A process and a device for coating a temperature-stable component with a thermal protection layer (15), in which the temperature-stable component has a surface (12) which is to be coated with the thermal protection layer (15) and at which there is at least one cooling-passage opening (1) which is connected to a cooling passage running inside the component. During the coating a mass flow (10) emerges through the cooling-passage opening (1), the coating takes place by a coating mass flow (11) directed onto the surface (12) which is to be coated, and the mass flow (10) emerges through the cooling-passage opening (1) and the coating mass flow (11) include an angle &agr;≠0°.

Abstract: The invention relates to a catalyzer for burning at least part of a fuel/oxidant mixture flowing through the catalyzer, in particular for a burner of a power plant installation. The catalyzer comprises several catalytically active channels and several catalytically inactive channels. A longitudinal section of the catalyzer is spaced apart from an inflow side in the main flow direction. In this longitudinal section turbulators are arranged in at least several catalytically active channels. In addition or alternatively, connections that enable a flow between the channels are formed in this longitudinal section between several adjoining channels.

Abstract: A device for fixing a ceramic component in a metallic support is provided. The device includes a bush, which is produced from gray cast iron with lamellar graphite, arranged at those locations of the ceramic component where the ceramic component is fixed in the metallic support. Internal oxidation of the gray cast iron with lamellar graphite attaches the ceramic component to the bush.

Abstract: A stator vane in an axial flow turbine can be fixed to the stator casing by means of force-fit attachment elements. The stator vane root has a hollow profile and includes radially inner platform matched to the contour of the flow channel, a radially outer platform matched to the contour of the stator casing, and two essentially parallel sidewalls. The outer platform has at least one hole for the attachment element. In one embodiment, the outer platform is detachably connected to the vane root. In other embodiments, a cavity is formed with vane root walls and with stator casing walls and is essentially tightly sealed from hot gas passing through the flow channel, allowing cooling of the cavity with little coolant loss, and allowing vanes without any seals between platforms and other vane root parts. In another embodiment, bearing surfaces of each vane are provided at different levels.

Abstract: In a turbo generator with a rotor with direct gas cooling, which rotor is provided with a rotor winding arranged around a central rotor body, said rotor winding being on the front sides covered by one each annular cap plate, and in which rotor cold cooling gas for cooling the rotor flows into ring gap segments between the cap plate and the rotor body, whereby the ring gap segments are bordered, when seen in circumferential direction, on the sides in each case by the section of an end spacer plate provided between the cap plate and the rotor winding, whereby this section is projecting into the ring gap, improved cooling is achieved in that separations of the cooling gas stream on flowing into the ring gap segments are avoided by designing the sections of the end spacer plates, whereby these sections adjoin the ring gap, in a manner that is advantageous with respect to the flow.

Abstract: The invention relates to a gas turbine seal, comprising a metallic component (1) with a durable or erosion-resistant ceramic coating (2) and an abradable ceramic layer (18) which is arranged thereon in locally delimited fashion, a bond layer (5) being arranged on the surface (4) of the metallic component (1), to which bond layer the durable or erosion-resistant ceramic coating (2) is applied as a covering layer. The invention is characterized in that the bond layer (5) comprises separate, adjacent spherical rivets (6) or mushroom-shaped rivets (6) which have a web (7) and a head (8). These rivets form individual metal islands with numerous undercuts (12), around which there is a continuous ceramic network. It is possible to produce very thick layers which have a good bond strength, the ceramic not being flaked away even in the event of introduction of radial/tangential forces, sickle-shaped contact or locally high overheating/frictional heat, and a good sealing action being achieved.

Abstract: In a method for controlling a steam turbine installation having a reheater (7) arranged between high-pressure turbine (2) and medium-pressure turbine (3) or low-pressure turbine (4), a low-pressure bypass (18) with a low-pressure bypass valve (19) also being present, which bypass leads from the reheater outlet into a condenser (5), a flexible and optimum control with respect to variable high-pressure turbine exhaust steam temperature (THD) is achieved in that characteristic curves for the required value of the reheater pressure are used for controlling the low-pressure bypass valve (19) during run-up, during (partial) load rejection procedures or during idling, which characteristic curves depend on the load (L) applied to the installation, and/or on the pressure (P) before the high-pressure turbine blading and/or on the reheater steam flow (M), and also on the high-pressure turbine exhaust steam temperature (THD), and/or on the temperature (TFD) and/or on the pressure (pFD) of the live steam introduced into t

Abstract: A method for increasing the efficiency of a steam generator system including a boiler and a regenerative air preheater. The method including determining a reduced rate of acid accumulation in the preheater which may be achieved by injecting an SO3 neutralizing additive material into flue gas generated by the boiler. A new maximum allowable clean condition pressure drop is calculated based on the reduced rate of acid accumulation. Modified heat exchange element baskets are created having an increased heat transfer efficiency, compared to conventional heat exchange element basket assemblies, and a maximum allowable clean condition pressure drop substantially equal to the calculated new maximum allowable clean condition pressure drop. The conventional heat exchange element basket assemblies are replaced with modified heat exchange element basket assemblies. When the boiler is operating, the additive material is added to the flue gas.

Abstract: A method of fitting an impingement plate to a platform of a guide blade of a gas turbine. The impingement plate is first fastened at individual spots by spot welds to at least one supporting surface of the platform and is then brazed at the supporting surface to the platform. The impingement plate is prefabricated with recesses and the spot welds are executed at the recesses.

Abstract: Described is a fixation device for blading of a turbo-machine, in which, longitudinally to a mounting groove (1), a plurality of blades (31, 32) is positioned, and in which, between at least two blades (31, 32) positioned adjacent to each other inside the mounting groove (1), a mounting gap is provided, having two insertion elements constructed as collar halves (41, 42) that can be inserted into the mounting gap, and each of which has a width adapted to the width of the mounting gap and which enclose between themselves a gap space (5) into which a wedge element (43) can be inserted that can be wedged in such a way that both collar halves (41, 42) are fixed in a force-derived manner by means of the wedge element (43) inside the mounting groove (1).

Abstract: A method of forming a curved cooling channel into a gas turbine component such as a turbine blade uses an electrode in the form of a helix. The electrode is driven to rotate around the central rotational axis of the helix and axially along the central rotational axis. A turbine blade for a gas turbine component is provided with at least one helical cooling channel.

Abstract: A method is disclosed for reducing the variance in the coolant consumption of components of a turbo-machine, in particular a gas turbine. The components are provided with one or more holes for the passage of a coolant, wherein a surface roughness existing inside the holes is reduced by mechanical finishing. The method is characterized by mechanical finishing that is performed by reshaping rough points that cause the surface roughness using a cold working process such as at least one of beating, pressing and rolling. The method permits a simple reduction of the surface roughness without creating finishing residues that could result in obstructions of the holes.

Abstract: A gas turbo set (1, 2, 3) is equipped with at least a cooling air system (20,21). Throttle points (22, 23) are arranged as throttling points in the cooling air flowpath, for the purpose of defining the cooling air mass flow. Said manifolds are bypassed by bypass lines (24). Means (25) are arranged in said bypass lines for adjusting the bypass mass flow. Thus, the cooling air mass flow can be varied without acting on the main cooling air flow as such.

Abstract: Described is a device and a method for cooling a platform of a turbine blade comprising a blade root, a vane with a leading and trailing edge, as well as a blade tip with a platform, through which platform extends radially, at least in part, at least one cooling channel that is connected with at least one outlet channel exiting via an outlet opening at the platform. The invention is characterized in that the outlet channel has, adjacent to the outlet opening, a longitudinal channel direction that extends, in projection, longitudinally to the turbine blade in an essentially co-parallel manner with respect to the flow direction of a local flow field of a mass flux relatively passing by the turbine blade, said flow field directly flowing over the exit opening.

Abstract: A cover for a heat exchange element basket assembly includes a metal sheet and at least one lifting lug. A vertical groove extends inward from the outer surface of the metal sheet. Each lifting lug is a horizontal plate having an opening extending vertically there through, an outer edge, and a shape which is substantially complementary to the cross-sectional profile of the groove. The lifting lug is mounted within the groove, such that the outer edge of the lifting lug does not extend beyond the outer surface of the metal sheet.