Abstract: In a gas turbine having sequential combustion and two combustion chambers and in each case associated turbines, a secondary guide row (6a-c) formed in an annular transition duct (1) is arranged on the downstream side of the first turbine before entry into the second combustion chamber. A number of blades of this secondary guide row effect an irrotational flow with regard to the mixing elements, which are located in the second combustion chamber and in the flow plane of the blades, which in each case are combined to form an assembly. Due to the irrotational incident flow in the second combustion chamber, the mixing elements produce a uniform separate swirl flow which optimizes the subsequent combustion, designed for self-ignition, with regard to efficiency and pollutant emissions.

Abstract: In a premix burner (18) having axial or radial air inflow, in which premix burner (18) the combustion air (15) flows out of a plenum (27), arranged before or around the burner (18), into the burner (18) and fuel (12, 13) is mixed with it on the way through the burner (18), a perforated component (24) having a wall thickness (s) and openings (25) of in each case a diameter (d) and at a distance (t) apart is arranged between the plenum (27) and the burner (18), which component (24) splits the combustion air (15) flowing through into small defined jets which reunite after a certain running length (l), the ratio of wall thickness (s) to the diameter (d) of the openings (25) being greater than/equal to one, and the ratio between the through-flow area of the component (24) and the possible inflow area to the burner (18) being greater than/equal to one as a function of the type of burner.

Abstract: In a combustion chamber (100) which is designed as an annular combustion chamber and a mixing essentially comprises a primary zone (1), a mixing section (2) arranged downstream and an adjoining secondary stage (3), vortex generators (200) are fixed inside the mixing section (2), which vortex generators (200) serve to form vortices. Both the mixing section (2) and the vortex generators (200) are provided with passage openings through which mixing air (8) flows into the interior of the mixing section (2) and mixes there with the main flow (4). The quantity of the intermixed mixing air (8) is variable; it can have a supercritical or subcritical blow-out rate relative to the main flow (4), and in this connection at least film cooling of the duct walls (5, 6) and of the vortex generators (200) takes place even at subcritical blow-out rate.

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 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 a combustion chamber (14) of a gas-turbine group which is arranged downstream of a first turbine (11) and upstream of a second turbine (12) and has a burnerless combustion space, extending between the outflow plane of the first turbine (11) and the oncoming-flow plane of the second turbine (12), and a fuel injector (2) which comprises a fuel-nozzle holder (8), extending transversely to the main flow (1) approximately up to the center axis, and a fuel nozzle (9) arranged in the direction of flow in the center axis and connected to the fuel-nozzle holder (8), the combustion chamber (14) working with premixing combustion, and the inlet temperature of the exhaust gas of the first turbine (11) into the combustion chamber (14) being above the self-ignition temperature of the fuel (13), the fuel injector (2) has means for simultaneously evening out the velocity profile and for lowering the temperature of the flow in the wake region.

Abstract: In a combustion chamber, a gaseous or liquid fuel is injected as a secondary flow into a gaseous, channelized main flow. The main flow is directed to pass over a plurality of vortex generators (9) arranged side by side over the width or circumference of the channel (20) through which the flow passes. The height (h) of the vortex generators is at least 50% of the height (H) of the channel through which the flow passes or of that part of the channel associated with the vortex generators. The secondary flow is introduced into the channel (20) in the immediate vicinity of the vortex generators (9). Longitudinal vortices without any recirculation region are produced in the channel through which the flow passes by means of the new static mixer. Extraordinarily short mixing distances, with a low pressure loss at the same time, are thus achieved in a combustion chamber according to the invention.

Abstract: In a combustion chamber which consists essentially of an inflow zone and a combustion zone, the working gases flowing at high temperature into the combustion chamber are mixed with a fuel, in such a way that the latter initiates auto-ignition. Whilst the inflow zone is cooled by effusion cooling, convective cooling is adopted in the combustion zone, the cooling air for the last-mentioned cooling being used at the same time as cooling air for the effusion cooling.

Abstract: In a gas turbine combustion chamber in which for cooling purposes use is made of combinations of convective heat transfer mechanisms whose basic principle is the elimination of heat by flow, the transition from the convective cooling channel (4) to the plenum upstream of the burners (5) is in the form of a small diffuser (6). The total pressure loss in the entire system is thereby reduced, thus leading to improved efficiency with minimum emissions.

Abstract: In a gas turbine combustion chamber, which consists of an inlet zone (1) with injection, an ignition delay zone (2), a reaction zone (3), a burn-out zone (4) and a transition zone (5) to the turbine, the reaction zone (3) has a cross-section which increases in such a way that the gas dynamics of the combustion process can take place at constant pressure or constant Mach number. By this means, the total pressure loss and the combustion chamber length necessary for the combustion are reduced and this is reflected in an improvement to the efficiency and the output.

Abstract: In a method and an apparatus for influencing the wake of combustion chamber inserts, a passage (5) for guiding an additional air mass flow (3) is arranged in the inserts (2), which passage is connected to outlet openings (6) which are arranged in the part of the inserts located opposite to the main flow (1). The additional air mass flow (3) is, for example, extracted from the combustion chamber cooling air (4), is guided through the passage (5) and is blown out through the outlet openings (6) before the actual combustion zone in such a way that the recirculating flow region is minimized in the wake of the inserts (2).

Abstract: In a gas turbine combustion chamber (1)--having environment-friendly burners (5) which consist of at least two hollow partial conical bodies which are positioned one upon the other in the flow direction and whose longitudinal axes of symmetry extend radially offset relative to one another, by which means tangential opposed-flow air inlet slots are produced for a combustion air flow, at least one nozzle for spraying in the fuel being placed in the hollow conical space formed by the cone-shaped partial conical bodies, and having a cooling duct (4), which is bounded by the combustion chamber inner wall (2) and the combustion chamber outer wall (3), along which the cooling air flows and in which longitudinal and transverse ribs (8) can be arranged--the cooling duct (4) has a continuously decreasing height and/or increasing surface roughness in the flow direction of the cooling air.

Abstract: In a gas turbine combustion chamber (1) cooled by means of impingement cooling, the height of the cooling duct (5) formed by the perforated plate (3) and the impingement surface (4) increases continuously in the transverse flow direction to correspond with the supply of cooling air. Tubes (7) are arranged in the cooling duct (5) on the holes (6) of the perforated plate (3) in such a way that the impingement air meets the impingement surface (4) at right angles, the height of the tubes (7) increasing in the transverse flow direction in such a way that the distance between the tubes (7) and the impingement surface (4) is constant over the complete length of the cooling duct (5). By this means, the heat transfer coefficient remains constant along the impingement cooling section and uniform removal of heat is made possible. The cooling effect can be specifically controlled by a suitable choice of the diameter of the holes (6) and the height of the tubes (7).