Abstract: A combustion chamber 10 for a gas turbine operates in a highly diluted mode of combustion has a substantially toroidal plenum 30. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flow 2 is established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of the gas re-circulation to allow for the onset of highly diluted combustion.

Abstract: A gas turbine arrangement with heat accumulation segments (3) which are arranged, opposite moving blades, on a casing of the gas turbine, and with guide vanes (1) which are arranged adjacently to the heat accumulation segments (3) over the circumference between the casing of the gas turbine and the rotor, the moving blades and the guide vanes (1) being arranged in a hot-gas duct (5) of the gas turbine. At least one sealing element (4) arranged over the circumference is present between the guide vanes (1) and the heat accumulation segments (3) and can be separated from the hot-gas duct (5) by means of a protective shield (6).

Abstract: A very simple and reliable process for cancelling the reaction field (10) induced by a rotor (4) is proposed, wherein the rotor (4) is rotating in a static magnetic field (7) in a static outer core (3), and wherein the rotor (4) comprises at least two conductors (6) aligned substantially parallel to the axis (8) of the rotor (4). The armature reaction (10) is cancelled by means of a set of auxiliary windings (11) located on the static outer core (3) wherein said auxiliary windings (11) are fed with a direct current (DC) cancelling the reaction field (10). Preferentially, the process is applied to a brushless exciter and the auxiliary windings (11) have the same geometry as the conductors (6) of the rotor (4) and are all equally fed with a direct current corresponding to the current induced in the conductors (6) of the rotor (4) when the rotor is rotating in the static magnetic field (7).

Abstract: A fixing method for blading of a fluid-flow machine, in which first of all the turbine blades (31, 32) are inserted into the fastening slot (1) of a rotor (2) or stator until only the intermediate fitting gap is left, into which two insert elements designed as end piece halves (41, 42) are then inserted. After that, a wedge (6) is inserted into the gap between the end piece halves (41, 42), and the end piece halves (41, 42) together with the wedge (6) are welded by a joining weld (10). With the method according to the invention and the arrangement according to the invention, axial forces which can warp the rotor (2) and thus cause increased rotor vibrations are advantageously avoided. The invention also relates to a fixing arrangement according to the invention.

Abstract: According to the invention, power matching in an electricity grid (N) is carried out by regulation of a storage power station (S) which is operated in the grid. In the event of changes in the power available or in the power consumption in the grid, the power consumption of the power consuming machine (V) in the storage power station is adapted so as to maintain equilibrium between the total power generation and the total power consumption. Power matching by regulation of the power load can be carried out around one order of magnitude more quickly than power matching by regulation of power generating machines (G1, G2, G3, GS) which act on the grid, and saves alternating thermal loads in the power stations.

Abstract: A method and a device for the introduction of fuel into a premixing burner, with a pilot gas feed and a premix gas feed for the operation of a gas turbine in the entire load range, in which the pilot gas feed is carried out via a burner lance provided in the premixing burner and the premix gas feed is carried out via side wall shells of the premixing burner. The premix gas feed and the pilot gas feed are carried out in combination, in such a way that a continuous mixture ratio between premix gas and pilot gas can be set within the premixing burner.

Abstract: A silencer (25a) for the attenuation of noise occurring in an intake airstream (10, 27) of a gas turbine (1–3) includes a device or devices (31, 32, 33, 34) for the introduction of water and/or steam into the intake airstream (10, 27). These devices may be designed, in particular, in the form of Venturi tubes (31), the water (29) being supplied, in particular above the saturation limit, to the airstream (27) via nozzles (33) arranged at the narrowest point. In this way, the silencing can be combined at the same time with the introduction of water for increasing the power output or for the general regulation of the gas turbine, this being achieved with a comparatively simple design.

Abstract: A fogging device (26) for introducing water and/or vapor into an intake air flow (10, 27) of a gas turbine (1–3) includes a sound-absorbing device (31, 35). This device may in particular be designed in the form of Venturi tubes (31), the water (29) being fed to the air flow (27) via nozzles (33) arranged at the narrowest location. In this way, the spraying of water for increasing the power output or for generally regulating the gas turbine can at the same time be combined with a silencer, and this in a comparatively simple construction.

Abstract: A description is given of a damping arrangement for reducing resonant vibrations in a combustion chamber (1), with a combustion-chamber wall (2), which is of double-walled design and, with an outer wall-surface part (22) and an inner wall-surface part (21) facing the combustion chamber (1), gastightly encloses an intermediate space (3), into which cooling air can be fed for purposes of convective cooling of the combustion-chamber wall (2). The invention is distinguished by the fact that at least one third wall-surface part (4) is provided, which, with the outer wall-surface part (22), encloses a gastight volume (5), and that the gastight volume (5) is connected gastightly to the combustion chamber (1) by at least one connecting line (6).

Abstract: The present invention describes a method for producing a target substance by utilizing a microorganism comprising culturing the microorganism in a medium, allowing the target substance to accumulate, and collecting the target substance from the medium. Also the microorganism used in the present invention is a mutant strain whereby maltose assimilation is controlled by the interaction between IIAGlc protein of glucose PTS and MalK.

Abstract: In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device (10) is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle (21) and heating it up to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube (19) arranged behind said nozzle (21), and using said heated-up gas to directly or indirectly ignite a fuel/air mixture introduced into said combustion chamber.

Abstract: The invention relates to a hybrid blade (1) for thermal turbomachines, having an airfoil (2) made of a metallic material of a certain density, and having a blade root (3). It is characterized in that the blade root (3), compared with the airfoil (2), is made of a different metallic material having a lower density, and in that the airfoil (20) is connected to the blade root (3) in a positive-locking manner. The blade in this case is advantageously a compressor blade, in particular a high-pressure compressor blade, in which the airfoil (2) is made of a stainless CrNi steel and the blade root (3) is made of a high-temperature titanium alloy or an intermetallic gamma titanium aluminide alloy or an intermetallic orthorhombic titanium aluminide alloy.

Abstract: In a method for producing a target substance utilizing a microorganism, which comprises culturing a ?-proteobacterium in a medium to produce and accumulate the target substance in the medium or cells and collecting the target substance, there is used a strain in which the ArcA protein does not normally function in the cell by means of, for example, disruption of the arcA gene on the chromosome.

Abstract: A compressor for a gas turbine has, on the surfaces of its components, in particular of its blading, a coating for protecting the surfaces from erosion. The coating has at least two layers or a plurality of pairs of layers formed from amorphous carbon or a plasma polymer, the layers having an inherently high hardness, and the outermost layer of the coating having hydrophobic properties. Furthermore, the hardness of an inner layer of a pair of layers is higher than the hardness of an outer layer. The coating is particularly suitable for the avoidance of drop impingement erosion caused by liquid drops, erosion caused by solid particles, such as ice, and contamination caused by deposition of dust particles and constituents which are dissolved in liquids. The coating prolongs the service life of the components and increases the power of the turbine.

Abstract: The present invention is directed to a highly reliable optical semiconductor device (1), which comprises an optical semiconductor chip (2) sealed in a surrounding soft resin (3) and in a hard resin (4) harder than the soft resin. The hard resin (4) has an aperture (7b) configured to relieve a state of hermetic sealing for the soft resin (3) and formed in a direction that imposes no optical influence on a function of the optical semiconductor chip (2). The soft resin (3) and the hard resin (4) are employed for double sealing to form the highly reliable optical semiconductor device (1) without providing any space. This is effective to solve a problem caused in a conventional optical semiconductor device associated with double sealing by soft and hard resins to increase reliability, which requires a space between both resins and results in deteriorated performance, for example, a reduced amount of light.

Abstract: In an emergency cooling system (17) for a component (1) which is subject to thermal load in operation, in, e.g., a turbine, the component (1) has a wall (3) which, in operation, is acted on by heat on a first wall side (14) and is acted on by a flow of cooling fluid (11) on a second wall side (15). The wall (3) has at least one emergency cooling opening (12) which is closed off by a plug (16) and through which cooling fluid flows from the second wall side (15) to the first wall side (14) when the plug (16) is absent. The plug (16) is designed so as to melt at a predetermined temperature. The plug (16) is a body which is produced separately from the component (1), the plug (16) being inserted into the emergency cooling opening (12), in which it is connected to the component (1).

Abstract: A description is given of a method for the analysis and/or monitoring of the partial discharge behavior of an electrical operating means, in particular in terms of its development over time. Here, appropriate partial discharge data is recorded in process state matrices (2, 3), in which, in each case in a matrix element (5) of the process state matrix (1), the amplitude (7) of a partial discharge, its phase angle (6) and its frequency of occurrence is depicted (in particular what is known as a PRPD representation). A simplified analysis is made possible by the fact that, at a first time, a partial discharge process state is registered in a first process state matrix (2) and, at a later time, a further partial discharge process state is registered in a further process state matrix (3). Then, for the purpose of analysis and/or monitoring, the first (2) and the second (3) process state matrix are compared with the aid of comparison and scaling methods.

Abstract: In a power generation unit, especially in a gasturbo group, a gaseous process fluid is guided in a closed cycle. The gaseous process fluid flows through a compression device (1), a heater (6) and an expansion device (2), especially a turbine. Downstream from the expansion device at least one heat sink (11, 13) is arranged in which the gaseous process fluid is cooled before it is returned to the compressor device (1). At least one heat sink includes a waste heat steam generator in which an overheated amount of steam (26) is generated that is added to the compressed gaseous process fluid. Together with the gaseous process fluid the steam flows through the heater (6) if necessary and is expanded together with it. The expanded steam condenses in the waste heat steam generator (11) and another heat sink (13); the condensate is processed in a filter (16) and is returned to the waste heat steam generator (11) under pressure via a feed pump (18).

Abstract: A gas turbo group has a combustion chamber comprising a catalytic burner stage (2), a preburner stage (1) located upstream from the catalytic burner stage, as well as a non-catalytic burner stage (11, 5, 6) located downstream from the catalytic burner stage. The preburner stage serves to always maintain a temperature (T1) at the inlet into the catalytic stage that corresponds at least to a minimum temperature (TMIN) necessary for operating the catalytic burner stage. According to the invention, the gas turbo group is operated so that the burner stage located downstream from the catalytic combustion chamber is taken into operation only when the temperature (T2) at the outlet from the catalytic stage has reached an upper limit in the presence of a maximum combustion air mass flow.

Abstract: Combustion driven pressure pulsations may limit the range of operating conditions where a modern gas turbine can operate with low emission and high efficiency performance. The control of acoustic vibrations has been consequently growing as an essential issue in gas turbine design, development and maintenance. The basic idea of the present invention is to use cooling air leakage through the gaps (7) of combustor liner segments (3;4) to get acoustic damping of combustion pulsations. The main component of the design is the sealing device (8) which covers the gap (7) between the two liner segments (3) and (4). The sealing device (8) collects in the plenum (9) some of the cooling air (6) flowing between the outer casing (1) and the inner liner structure (2). For this purpose the sealing device (8) is provided with openings (12) along the side walls (10) which allow the cooling air (6) to enter the plenum (9).