Abstract: In a turbo set (100) with a starting device (120), the turbo set includes a compressor (102), a combustion chamber (103) and a turbine (104) and also a generator motor (108) which is drive-connected to the turbine (104). The starting device (120) serves for starting the turbo set and includes a steam generator (121) for the generation of steam which is under overpressure, a steam turbine (129) and an auxiliary generator (130). The steam generator (121) and the steam turbine (129) are connected to one another via a first supply line (125a) for the supply of steam generated in the steam generator (121) to the steam turbine (129). The auxiliary generator (130), on the one hand, is drive-connected to the steam turbine (129) and, on the other hand, for the transmission of electrical power from the auxiliary generator (130) to the generator motor (108), is electrically connected to the generator motor (108).

Abstract: A power plant comprises a gas turbo group with a heat transfer apparatus, for example a recuperator for the preheating of the combustion air, arranged downstream of the turbine in the smoke gas path of the gas turbo group. A smoke gas purification catalyst is arranged downstream of at least part of the heat transfer apparatus, at a point at which the smoke gas is already cooled as a result of heat exchange to an extent such that irreversible damage to the catalyst due to overheating is avoided. On the other hand, the point is selected such that a temperature necessary for maintaining the catalytic smoke gas purification is ensured. In a preferred embodiment, a temperature measurement point is arranged, at which the temperature of the catalyst or of the smoke gas flowing into the catalyst is determined, so that this temperature can be regulated by means of suitable regulating actions.

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: 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 compressed air energy storage power station comprises a first shafting (1) and a second shafting (2). A gas turbo group (11), an electrical machine (12) and a compressor (13) are arranged on the first shafting (1). Switchable clutch elements (14, 15) are arranged between the electrical machine and the gas turbo group or the compressor. The clutch elements allow a connection to be selectively made between the electrical machine and the gas turbo group (11) or the compressor (13). An expansion machine (21) for the power generating expansion of a pressurized storage fluid, an electrical machine (22) and a compressor (23) are arranged on the second shafting (2). Switchable clutch elements (24, 25) are arranged between the electrical machine and the expansion machine or the compressor and allow the electrical machine to be optionally connected to the expansion machine and to the compressor. The electrical machines are operable both as generators and as electric motors.

Abstract: A storage power station (S), for example an air storage plant, that includes a compressor unit (V), a turbine unit (T) and a storage volume (100) can be operated using a specific method of operation, which allows as fast a reaction as possible to changes in the load demands. Rapid changes in the load demands can be satisfied by controlling the power consumption of the compressor unit (V), which results in a variable net power output, with the power output from the turbine unit (T) remaining constant. The power of the compressor unit can be controlled approximately one order of magnitude more quickly than the power generation machine can be controlled. In the extreme, the compressor unit can simply be shut down, thus resulting in its drive power becoming available to an electricity grid within seconds. During this process, the turbine unit can continue to operate normally, and can slowly follow the power demand, thus reducing the load on the turbine.

Abstract: A CAES plant comprises an atmospheric combustion chamber situated downstream from the expansion machine. The flue gas produced in the process passes through a heat exchanger. In the heat exchanger, the storage fluid, which flows to the expansion machine from the storage, is heated by heat exchange. In the inventive power plant, the storage fluid is used directly for combustion of a fuel without exposing the expansion machine to corrosive flue gases.

Abstract: In a method of operating a gas turbine group with low calorific value fuel, the gas turbine group essentially comprises a compressor, a combustion chamber, a turbine and a generator. The low calorific value fuel is compressed by means of a fuel compressor. Low calorific value fuel (11a) in excess of the stoichiometric quantity is mixed into part of the combustion air (9, 9a) during the starting of the gas turbine group so that a stable flame appears. After the attainment of the rated rotational speed (B) and synchronization, at the latest, the quantity of low calorific value fuel (11a) is reduced to such an extent that a ratio is attained which is just over the stoichiometric ratio. The rest of the low calorific value fuel (11b) is mixed into the rest of the combustion airflow (9a, 9b) in order to attain the desired load.

Abstract: A combustion chamber with two-stage combustion has primary burners (110) of the premixing type of construction, in which the fuel injected via nozzles (117) is intensively mixed with the combustion air inside a premixing space (130) prior to ignition. The primary burners are of flame-stabilizing design, i.e. they are designed without a mechanical flame retention baffle. They are provided with tangential inflow of the combustion air into the premixing space (130). Arranged downstream of a precombustion chamber (61) are secondary burners (150) which are designed as premixing burners which do not operate by themselves.

Abstract: In a gas turbine combustion chamber cooled by means of impingement and convection cooling or pure convection cooling, a compensating flow of the cooling air is guided between adjacent cooling ducts (2) in such a way that the flow velocity in the cooling duct (2) always exceeds a critical limiting value even downstream of a local damage location (6) so that the temperature is less than a critical limiting value. The compensating flow is led past the combustion chamber outer wall. Connecting openings (5) are arranged between adjacent cooling ducts (2) and are respectively offset on the opposite sides of the cooling duct (2).

Abstract: The annular chamber of a heat generator for generating of hot gas, which is placed downstream of a fluid flow engine and upstream of a turbine, is defined by an exterior wall and an interior wall which extend approximately axially. The exterior wall and the interior wall are connected with each other by a plurality of supports extending radially. These supports have in their interior at least one supply conduit for a fuel and at least one further conduit for conveying an air flow. Furthermore, the supports also have a plurality of fuel nozzles, through which the fuel/air mixture is introduced into the annular chamber.

Abstract: In a cooled wall part having a plurality of separate convectively cooled longitudinally cooling ducts (2) running near the inner wall (1) and parallel thereto, adjacent longitudinal cooling ducts (2) being connected to one another in each case via intermediate ribs (3), there is provided at the downstream end of the longitudinal cooling ducts (2) a deflecting device (4) which is connected to at least one backflow cooling duct (6) which is arranged near the outer wall (5) in the wall part and from which a plurality of tubelets (7) extending to the inner wall (1) of the cooled wall part and arranged in the intermediate ribs (3) branch off. By means of this wall part, the cooling medium can be put to multiple use for cooling (convective, effusion, film cooling).

Abstract: In a gas-turbine group which is operated with sequential combustion, preferably via two combustion chambers (4, 9) having in each case turbines arranged downstream, the temperature of the exhaust gases (8) from the first turbine (5) is recorded directly in front of the self-ignition point in the second combustion chamber (9) for the dosing of the fuel quantity for the first combustion chamber (4). The temperature is recorded by means of thermocouples (17) which are integrated in fuel lances (16) of the second combustion chamber (9), as a result of which influence is at the same time exerted on the fuel quantity (10) of this combustion chamber (9).

Abstract: In a gas turbine combustion chamber cooled by means of impingement and convection cooling or pure convection cooling, a compensating flow of the cooling air is guided between adjacent cooling ducts (2) in such a way that the flow velocity in the cooling duct (2) always exceeds a critical limiting value even downstream of a local damage location (6) so that the temperature is less than a critical limiting value. The compensating flow is led past the combustion chamber outer wall. Connecting openings (5) are arranged between adjacent cooling ducts (2) and are respectively offset on the opposite sides of the cooling duct (2).

Abstract: In the case of a combustion chamber which is respectively arranged upstream of and downstream of a fluid-flow machine and which essentially comprises an inflow duct (5) and a downstream premixing and combustion zone (5a), a fuel (11) is injected into the combustion air (4) coming from the fluid-flow machine acting upstream after the combustion air (4) flows through vortex generators (200). The injection (7a, 7b) of the fuel (11) into the premixing and combustion zone (5a) is effected in varying direction and quantity. The hot gases from the combustion of the aforesaid mixture form a temperature-graduated front (8), the minimum temperature of which corresponds fluidically with the base of the blades to be acted upon of the fluid-flow machine (2) . arranged downstream. The fuel (11) can be assisted with assisting air (12).

Abstract: A method and apparatus for operating a combustion chamber for autoignition of a fuel includes spraying fuel into a hot gas through a plurality of fuel lances disposed in a mixing zone of a combustion chamber for autoignition of the fuel. The fuel lances are supplied with fuel as two individually supplied groups. Fuel is supplied first to a first group of lances and increased to reach an intermediate operating temperature of about 1100.degree. C. The fuel supply to the second group is then activated, and the fuel supply increased to reach the same intermediate operating temperature with the second group. After both groups are operating at the intermediate temperature, the fuel supply to both groups is simultaneously increased to reach the operating temperature of the combustion chamber.

Abstract: In a combustion chamber consisting essentially of an inflow zone (5) and a combustion zone (11) and having self-ignition, the inflow zone (5) has vortex generators (100), of which a plurality are arranged next to one another over the periphery of the duct through which flow occurs. A premixing zone (7) follows downstream of the inflow zone (5), into which premixing zone (7) a gaseous and/or liquid fuel (9) is injected as secondary flow into a gaseous main flow (4). Between premixing zone (5) and the downstream combustion zone (11), the transition is characterized by a jump (12) in cross-section which induces the initial cross-section of flow of the combustion zone (11).

Abstract: In the combustion chamber of a gas turbine, at least one premixing burner (110) is arranged in a dome (51) communicating with a plenum (50). Said premixing burner (110) is fastened on the outlet side to a front plate (52) limiting the combustion space (58) of the combustion chamber. The premixing burner procures the combustion air from the dome. The fuel injected via nozzles is intensively intermixed with the combustion air within a premixing space of the burner prior to ignition.There is provided a jet injector (53) which opens into the dome (51) and of which the central nozzle (54) is connected to the combustion space (58) via an orifice (55) in the front plate (52) and of which the annular space (56) surrounding the central nozzle is loaded with a propellant.

Abstract: In a gas turbine group which consists essentially of a compressor (2), a first combustion chamber (3), a first turbine (4), a second combustion chamber (5) and a second turbine (6), the first combustion chamber (3) is configured as an annular combustion chamber. This annular combustion chamber (3) is operated by a number of premixing burners (11) which are distributed at the periphery. The first turbine (4) is designed in such a way that its exhaust gases have a temperature level which is above the self-ignition temperature of the fuel (13) used in the second combustion chamber (5). This second combustion chamber (5) consists of a burnerless, annular combustion space in which a number of vortex-generating elements (14) are integrated. The turbomachines, namely compressor (2), first turbine (4) and second turbine (6) are disposed on a rotor shaft (1), this rotor shaft (1) being supported in two bearings (9, 15).

Abstract: A premixing burner comprises a pilot burner (101) operating on the double-cone principle and a plurality of main burners arranged around the pilot burner. A gaseous and/or liquid fuel is injected into the main burner (52), which has a circular duct (20), as a secondary flow into a gaseous main flow. The main flow is first of all guided over vortex generators (9), a plurality of which are arranged next to one another around the circumference of the duct (20) through which flow takes place.