Abstract: A method of producing helical springs by spring winding with a numerically controlled spring winding machine includes feeding a wire, controlled by an NC control program, through a feed device to a forming device of the spring winding machine, forming a helical spring from the wire with the forming device, measuring an actual geometry of the helical spring to obtain actual spring data, comparing the actual spring data with nominal spring data to determine discrepancy data which represents a discrepancy between an actual geometry and a predetermined nominal geometry of the helical spring for at least one spring geometry parameter, analyzing the discrepancy data and producing correction data when discrepancies are outside selected predetermined tolerance limits, varying an actuating movement of at least a portion of the forming device on the basis of the correction data for producing a next helical spring, selecting a spring section, determining a correction value for an actuating movement of a portion of the f

Abstract: A method to control NH3 slippage and NOx conversion in an electronic controlled internal combustion engine exhaust system equipped with a selective catalyst reducer, a diesel particulate filter, a diesel oxidation catalyst and a urea doser.

Abstract: A method to operate an internal combustion engine with a diesel particulate filter to extend the life of the diesel particulate filter by initiating active regeneration of the diesel particulate filter when the soot load of the filter exceeds a predetermined actual soot load value.

Abstract: A method of producing helical springs by spring winding with a numerically controlled spring winding machine includes feeding a wire, controlled by an NC control program, through a feed device to a forming device of the spring winding machine, forming a helical spring from the wire with the forming device, measuring an actual geometry of the helical spring to obtain actual spring data, comparing the actual spring data with nominal spring data to determine discrepancy data which represents a discrepancy between an actual geometry and a predetermined nominal geometry of the helical spring for at least one spring geometry parameter, analyzing the discrepancy data and producing correction data when discrepancies are outside selected predetermined tolerance limits, varying an actuating movement of at least a portion of the forming device on the basis of the correction data for producing a next helical spring, selecting a spring section, determining a correction value for an actuating movement of a portion of the f

Abstract: A forming machine for producing formed parts by forming wire, tube or other elongated workpieces has a plurality of driven machine axes, a drive system having a plurality of electrical drives for driving the machine axes, a control device for the coordinated control of operating movements of the machine axes in a production process according to an operating program specific to the production process, and a speed setting device for setting the operating speed of the forming machine for the production process. An operator information system is used to determine and output at least one item of operator information which makes it possible for the operator to control the operating speed with respect to at least one control criterion which represents the energy consumption required for production.

Abstract: A method to control NOx slippage in an electronic controlled internal combustion engine exhaust system equipped with a selective catalyst reducer (SCR) and a urea doser.

Abstract: The disclosed embodiments relates to a method and an apparatus for determining the interfering field strength in an aircraft and the impairment of an electric system in the aircraft including cables between the outer shell and the interior panelling of the fuselage for transmitting signals within the aircraft. In order to enable direct and reliable determination of interfering field strength in an aircraft and assessment of the electromagnetic vulnerability of the communications system in the aircraft depending on the results of the determination, either a predetermined transmission signal is fed in at least one leaky line between outer shell and panelling of the fuselage and the reception signal that is irradiated by the leaky line is received with a receiver, or a predetermined transmission signal is transmitted with a transmitter and the reception signal is extracted from the leaky line. Subsequently the amplitudes of the transmission and the reception signals are compared with each other.

Abstract: The disclosed embodiments relates to a method and an apparatus for determining the interfering field strength in an aircraft and the impairment of an electric system in the aircraft including cables between the outer shell and the interior paneling of the fuselage for transmitting signals within the aircraft. In order to enable direct and reliable determination of interfering field strength in an aircraft and assessment of the electromagnetic vulnerability of the communications system in the aircraft depending on the results of the determination, either a predetermined transmission signal is fed in at least one leaky line between outer shell and paneling of the fuselage and the reception signal that is irradiated by the leaky line is received with a receiver, or a predetermined transmission signal is transmitted with a transmitter and the reception signal is extracted from the leaky line. Subsequently the amplitudes of the transmission and the reception signals are compared with each other.

Abstract: A method for producing hollow blade blades, in particular for gas turbines such as aircraft jet engines is provided. At least three elements (20, 21, 22) are located one on top of the other in a sandwich structure, are joined together at least in sections by diffusion welding and are then superplastically formed by expansion in such a way that a first element (20) forms a first external wall of the hollow blade to be produced, a second element (22) forms a second external wall of the hollow blade to be produced and a third element (21) forms a central element running between the two external walls of the hollow blade to be produced. At least one nick-minimizing structure is introduced into the first element (20) and the second element (22), which form the two external walls of the hollow blade to be produced, before said elements are arranged together with the third element (21) in the sandwich structure.

Abstract: A rotor for a propulsion plant has hybrid rotor blades arranged circumferentially around and extending essentially radially from a rotor. To reduce vibrations, the rotor blade has a metallic blade root and each blade has a metallic blade section that forms at least a portion of the blade leading edge and the area of the blade surface adjacent to the blade leading edge, and a blade section made of fiber-reinforced synthetic material or composite material. The blade sections (3, 4) of each blade (1) are so correlated to each other that damage or loss of the composite material blade section (4) still enables the propulsion plant to deliver a required emergency power.

Abstract: A rotor of a turbomachine includes blades having an improved blade root configuration for anchoring and centering the blade roots in axial slots of the rotor disk. Each blade root includes two portions or sections, namely a serrated section that has a single bilaterally uniformly shaped serration, and a terminal portion that has rounded surfaces and a narrower cross-section than the serrated root section. The serrated section provides anchoring against centrifugal forces. The terminal portion provides the predominant centering effect, for which it is radially movably received and located in a recess provided in the bottom of the slot. The special root configuration substantially avoids misfit and centering problems associated with manufacturing variances, whereby the blades and blade roots can be made of lightweight engineering materials.

Abstract: A method is provided for manufacturing a bladed ring for drum-shaped rotors of turbomachinery, especially rotors for axial compressors of gas turbine engines. The bladed ring is to be manufactured by hot isostatic pressing (HIP) and the fiber rings are formed in a metallic powder material for the bladed ring arranged in a circumferential direction. The fiber rings are bonded with spacing therebetween. The fiber rings are reinforced by fibers embedded in a metal matrix. The bladed ring prefabricated in this fashion by HIP is machined down to its required dimensions.

Abstract: A compressor impeller has a ring-shaped shroud band which is mounted at blade tips, each blade tip being enclosed in an identical radially slidable manner by a guide block, and the guide blocks being fastened to the shroud band. As a result, a narrow sealing gap and thus lower aerodynamic losses can be implemented than in conventional compressors, and the different centrifugally and thermally induced expansions of the blade and of the shroud band can be compensated.

Abstract: A hot gas overheat protection device is provided for gas turbine engines and the like. An outer metal wall having cooling air supplied through cooling holes therethrough from the outside is shielded from hot gas flow by the provision of highly temperature resistant lining wall elements spaced from the metal wall. A thin metal skin is provided between the metal wall and the wall elements defining intermediate spaces communicating with cooling air ports in the metal wall. The thin metal skin has a melting point equal to or lower than that of the metal wall so as to provide for fusion or rupture of the thin metal skin in the event the insulating wall elements are locally ruptured, whereby the cooling air is provided through the cooling air ports in a direction against the flow of hot gases to thereby mitigate the effects of the rupture and protect the metal wall.

Abstract: A combustion chamber arrangement for gas turbine propulsion units with a flame tube of ceramic material which is surrounded by a metallic wall while leaving free an intermediate space; the flame tube is composed of ring-shaped parts whereby sheet metal mounting members are so arranged between the outer walls of which and the metallic walls, especially of a housing without heat contact to the parts of the flame tube that a first and a second intermediate space for peripheral partial flows of cooling air is formed.