Abstract: The rotor (1) of a compression-wave engine has cells (6) on its periphery which are concavely curved on the two end faces of the rotor (1) inwards towards its center and towards the rotor axis. Consequently, the absolute trajectory of a particle runs from its entry point (7) into a cell (6) up to its exit point (8) therefrom in a virtually rectilinear fashion, whereby in the scavenging process the mixing zone between the two media participating in the compression-wave process, and thus the scavenging losses, are greatly reduced by comparison with straight cells.

Abstract: In premixing-type combustion of liquid fuel in a burner without a premixing section, a conical column (5) of liquid fuel is formed in the interior (14) of the burner, which column widens in the direction of flow and is surrounded by a rotating stream (15) of combustion air which flows tangentially into the burner. Ignition of the mixture takes place at the burner outlet, a backflow zone (6) forming in the region of the burner outlet. The burner itself consists of at least two hollow part-cone bodies (1,2) which are superposed on one another and have a cone angle increasing in the direction of flow. The part-cone bodies (1, 2) are mutually offset, so that tangential air inlet slots (19, 20) are formed. A nozzle (3) placed at the burner head ensures injection of the liquid fuel (2) into the interior (14) of the burner.

Abstract: Instead of labyrinth seals, ordinary circular cylindrical gaps (10, 18) are provided at the positions to be sealed in the contactless centrifugal seal device for, in particular, radial turbo-machines. By means of swirl fins (12) on shrouds (7) of the rotor (2), vortex flows which rotate like solid bodies along with the rotor (2) are induced in the vortex chambers (11), the rotational motion of the particles of the medium in the radial-axial planes being reduced to a thin boundary layer. By this means, the same pressure gradient appears outside the rotor (2) in the vortex chambers (11) between the gaps to be sealed (10, 18) as appears within the rotor (2) over the length of the vane passages (4) so that leakage flows are prevented.

Abstract: For the purpose of muffling low-frequency sound waves such as occur in components of fluid-flow engines, the muffler proposed here consists of a feed pipe (1) through which (3) and around which (4) a medium flows. At its end in the direction of flow, the feed pipe (1) has a row of muffling bore holes (2) distributed over the periphery, via which the medium (4) flowing around the feed pipe (1) flows into the interior of the feed pipe (1). The effective length L of the feed pipe (1), the cross-sectional area A of the feed pipe (1) and the total cross-sectional area B of the muffling bore holes form the geometric parameters for calculating an optimum muffling of the low-frequency sound waves.

Abstract: The pre-combustion chamber (1), in which liquid fuel is burnt sub-stoichiometrically, is connected upstream of a secondary combustion chamber (16), in which complete combustion takes place over-stoichiometrically. The sub-stoichiometric quantity of combustion air (11) for the pre-combustion chamber (2) is injected close to the wall from the outlet duct (3) upwards into the casing (2), which has a heart-shaped axial cross-section. The injection nozzles (7) for the fuel are positioned so that the jets of fuel (8) shield the layer of combustion air close to the wall from the partially burnt combustion mixture flowing through the outlet duct (3) into the secondary combustion chamber (16). At the end of the outlet duct (3) the quantity of auxiliary air required for complete combustion in the secondary combustion chamber (16) is added to the partially burnt combustion mixture.

Abstract: The atomizer nozzle exhibits an internal chamber (1) and an external chamber (2) which surrounds the latter in the form of a jacket, which chambers are provided with several outlet openings (9, 10 and 11, 12) which are in alignment in each case. A proportion of the atomizer air supplied via an air duct (5) flows into the internal chamber (1) and is essentially used there for uniformly distributing a liquid fuel, which is also flowing into the internal chamber (1) from a fuel duct (3), to its outlet openings (9, 10). The remaining greater proportion of the atomizer air flows around the internal chamber (1) through the external chamber (2) and is concentrically mixed in with the coarsely atomized fuel emerging from the outlet openings (9, 10) of the internal chamber (1). This prevents liquid fuel fragments from coming into contact with the walls of the outlet openings (11, 12) of the external chamber (2), and a high atomization quality is achieved.

Abstract: In the method, a process medium (14) is heated in two stages, in which fuel oil and gas premixed with air in a burner device (1) are partially burnt in a preliminary combustion chamber (12) substoichiometrically with an air coefficient (.lambda.) of approximately 0.7. The partially burnt mixture, which is low in nitrogen oxides, reaches a temperature of 1800.degree.-1900.degree. C., heats the process medium (14), which is already preheated to an intermediate temperature, to its final temperature in a heat exchanger (13) with counter-current flow and is cooled to 700.degree.-900.degree. C. In an air injection region (15) of the process heat generator the partially burnt mixture is mixed with quenching air in a stoichiometric ratio with respect to the unburnt fractions and is thereby completely burnt in a secondary combustion chamber (18) during which practically no nitrogen oxides (NO.sub.x) are produced. It reaches a temperature of 900.degree.-1300.degree. C.

Abstract: The present invention relates to a burner system, in particular for a gas turbine, with a main supply channel (2), debouching into a combustion chamber (1), for a fuel/air mixture having a swirler (5) and a burner lance (3) which passes through the swirler (5). To improve the transverse ignition properties between several such burner systems, optionally disposed on the burner chamber (1), and also to increase the flame stability, the burner lance (3) has, on the combustion chamber side with respect to the swirler (5) exit openings (12, 16) for fuel supplied to its interior or for a fuel-rich fuel/air mixture supplied to, or formed in, its interior.

Abstract: The resonance atomizer (4) of the burner facility has, as main components, a resonator ring (16) and a resonator cone (23), which each have an annular groove (25+24, respectively), which together form a resonance chamber (24+25). By a plurality of spacer strips (26) on the resonator ring (16), the resonator ring (16) and the resonator cone (23) are held apart by a distance which creates an annular inflow duct (27) for the oil/atomizing air mixture and outflow ducts (28) on the combustion space side for this mixture atomized in the resonance chamber (24+25). Between the components (16, 23) forming the resonator chamber (24+25) and the oil nozzle (7) there is an atomizing cross (17) with a baffle plate (19).

Abstract: In the combustion space of a combustion chamber of a gas turbine operated with liquid fuel, at least one after-burner (4) is employed in each case in combination with one or more primary burners (2, 2a). The after-burner (4) and at least its fuel spray cone (15), which acts directly into the central combustion chamber (6), are screened by an unswirled enveloping airstream (14) against the hot gases (13) from the combustion in the primary burners (2, 2a). The after-burner (4) itself is not automatically operating, i.e. the ignition of its mixture (14/15) takes place further downstream, preferably at the beginning of the mixing chamber (7), as a result of which a turbulence-free flow with uniform pressure and temperature profile is provided for acting on the turbine (9).

Abstract: In the dual burner of a gas turbine or a hot gas generating system, the swirler (1) is formed from at least two doubly curved sheets (4, 5) subject to tangential air inlet (7). These sheets (4, 5) are folded along diagonals (10a, 10b) running conically outwards in the outlet flow direction. One curved fold face forms an inner cone (4b, 5b) expanding in the direction of the swirler outlet end while the other curved fold faced forms an outer cone (4a, 5a) which contracts in the direction of the end outlet. The inner cones (4b, 5b) each carry at their ends a fuel main (8) whose fuel nozzles (9) are directed radially inwards towards the inner zone of the swirler (1). The liquid fuel (2a, 2b) is directed onto the outer cone (4a, 5a), the oil film (6) forming there being "rolled in" by the air (7) flowing into the outer cone (4a, 5a).

Abstract: The combustion chamber is characterized by an annular-cylindrical space, which consists of two reaction chambers (8), arranged at the end, and a collision chamber (12) placed therebetween. The reaction chambers (8) are fitted at their face-sided ends with a number of burner elements (A, B), arranged axially parallel, their number depending on the output of the combustion chamber, which burner elements are in each case mirror-symmetrical to each other in relation to the central axis of the collision chamber (12). From the collision chamber (12), an annular mixing chamber (15) goes off to the turbine inlet (17). Each burner element (A, B) is provided with a twist member (6, 11), which in each case is orientated in opposed sense of rotation compared with the mirror-symmetrically arranged twist member.

Abstract: An exhaust plenum chamber for a supercharged engine having a variable volume. A mechanical spring is arranged to an exhaust plenum chamber to increase the spring action of the plenum chamber volume. In this connection, the plenum chamber interior is divided into a flow chamber and a dead volume. The efficiency especially of relatively small plenum chambers in internal combustion engines with a small number of cylinders and/or slight supercharging is improved.

Abstract: A method and device for removing solid or liquid particles contained in suspension in a gas stream by an electric field, wherein the gas stream flow is directed past ion sources which simultaneously act as field electrodes. The suspended particles are thereby changed in a bipolar manner, such that approximately half of the particles are positively charged and the other half negatively charged, and are forced by the electric field to migrate across the gas stream into a preferred neutralization zone where they are concentrated, discharged, partially agglomerated and coagulated. Subsequently, the particle-enriched and particle-depleted partial gas stream thus formed are separated and treated further in accordance with operating requirements. Thereby the remaining gas stream maximally loaded with particles is fed into a particle-removal device where their withdrawal occurs.

Abstract: The high pressure compressor part of a gas turbine installation having a high pressure, a medium pressure and a low pressure part (21 and 22, 23) of the gas turbine is provided by a pressure wave machine in which the high pressure gas is generated by self-ignition of liquid or gaseous fuel, which is injected or blown into the cell rotor in the region of the low pressure air port from the fuel nozzles in a casing of the pressure wave machine. The self-ignition occurs as a detonation when the fuel impinges on a compression wave occuring in the region of the fuel injection. The pressure waves occuring generate, on the one hand, high pressure air in the zones (B) and (C), which are fed through a high pressure air port to a combustion chamber for the generation of driving gas for the gas turbine.

Abstract: Rotary flows are generated in a variety of technical installations.In these uses, the particular properties of the rotary flows generated and consequently those of the swirl generator itself play an essential part. Thus, for example in burner construction, a swirl is imparted to the combustion air, in order, on the one hand, to accelerate mixing between the fuel and air and, on the other hand, to utilize a possible return flow to improve the ignition condition.One question, among others relating to the design of the swirl generator, is to decide which flames with which properties are produced by the burner.It is therefore desirable, for control and optimization of the flame properties, to have available a swirl body of variable swirl intensity and swirl distribution.For this purpose, the swirl body (1) is equipped with several exchangeable guide blades (4) which are pushed in through a slotted outer tube (2) radially and at a pitch angle (.theta.).

Abstract: A pressure exchanger, preferably usable as a high-pressure compressor for gas turbine installations, has a multiplicity of coaxial cell rotors which can be driven in the same direction, and a central pressure exchanger combustion chamber located within the innermost cell rotor. Driving gases generated in the combustion chamber flow through the cell rotors in series from inside to outside and can be expanded as low pressure driving gases in the low pressure part of the turbine. The air to be compressed flows through the cell rotors in series from the outermost cell rotor towards the inside. A part of the air mass flow compressed to the final pressure, which part is greater than the driving gas mass flow, arrives as combustion air in the pressure exchanger combustion chamber; the other part of the air can be used as combustion air for a turbine combustion chamber, which generates high pressure driving gas for the gas turbine.

Abstract: An apparatus for cooling the charging air of a supercharged internal combustion engine wherein a part of the charging air delivered by the charger is branched off and is accelerated to supersonic velocity in a Laval nozzle. With the accelerated air, surrounding air is sucked in according to the principle of a jet pump. The mixture which forms flows through the heat exchanger, in which it takes up heat from the charging air flowing around the tubes, and thereafter is discharged to the surroundings.

Abstract: Very finely granular metal powders are produced by atomizing a liquid jet of metal by means of a gas jet which, in addition to a continuous band of sound frequencies, contains at least one discrete sound frequency which is at least 5 decibel above the average intensity of this band, and which is generated in a rotationally symmetrical device by means of a nozzle (4) which has the shape of a hollow cone and by means of an annular resonance space (7) with an annular edge (6) and is projected concentrically against the liquid jet of metal at a total opening angle of an average 35.degree. to 55.degree.. The atomization zone of the gas jet should preferably contain at least three discrete sound frequencies which are each at least 10 decibel above the sound intensity of the continuous band.

Abstract: Very finely granular metal powders are produced by atomizing a liquid jet of metal by means of a gas jet which, in addition to a continuous band of sound frequencies, contains at least one discrete sound frequency which is at least 5 decibel above the average intensity of this band, and which is generated in a rotationally symmetrical device by means of a nozzle (4) which has the shape of a hollow cone and by means of an annular resonance space (7) with an annular edge (6) and is projected concentrically against the liquid jet of metal at a total opening angle of an average 35.degree. to 55.degree.. The atomization zone of the gas jet should preferably contain at least three discrete sound frequencies which are each at least 10 decibel above the sound intensity of the continuous band.