Abstract: An apparatus and method for active gap monitoring for a continuous flow machine, in particular an aircraft propulsion device, which has a rotor and a housing which surrounds the rotor forming a rotor gap, is disclosed. The apparatus having a cooling channel which is arranged on the external circumference of the rotor housing and is supplied with cooling air from a plenum. The cross section of the cooling channel decreases from the plenum in the circumferential direction. This ensures homogenous cooling and reduces the weight of the apparatus.

Abstract: A method for repairing gas turbine components, in particular gas turbine blades, including at least the following steps: a) preparing a gas turbine component to be repaired; b) removing a damaged portion from the gas turbine component to be repaired, thereby forming a plane separation surface; c) placing the gas turbine component at least partly in a process chamber in such a way that the plane separation surface extends approximately horizontally within the process chamber; d) filling the process chamber with a metal powder that is bonding-compatible with the material of the gas turbine component to be repaired, namely up to the level of the separation surface; e) building up the removed portion on the separation surface by depositing metal powder in layers onto the separation surface and by fusing the metal powder, which has been deposited in layers onto the separation surface, to the separation surface.

Abstract: Proposed is a method for monitoring a passive pressure limiting valve (11) via which fuel is discharged from the rail (6) of a common rail system into the fuel tank (2), in which method, upon the detection of a defective rail pressure sensor (9), a switch is made from a rail pressure regulation mode into an emergency mode, wherein in the emergency mode, the rail pressure is successively increased until the pressure limiting valve (11) reacts, in which method, in the emergency mode, the pressure limiting valve (11) is set as open when the starting phase of the internal combustion engine has additionally been detected as having ended, and in which method, in addition, the opening duration of the pressure limiting valve (11) is monitored.

Abstract: A gas mixer for mixing a first gas and a second gas, including a gas housing, a Venturi tube, a flow body for the first gas arranged in the Venturi tube to form a mixing gap, an inflow tube connected to the Venturi tube, to an inflow opening to the Venturi tube for the second gas, and an actuating element for varying the inflow cross section of the inflow opening. The actuating element has a first and a second actuating part which restrict the inflow cross section. The first actuating part is a first gas housing part and the second actuating part is a second gas housing part. At least one of the gas housing parts forms part of the Venturi tube and/or of the inflow tube At least one of the gas housing parts can be moved with respect to another and has a rotor of a linear motor.

Abstract: In a method tor the emergency cooling of a battery or an emergency extinguishing of the battery of a water vehicle including such a battery with a watertight containment, upon determination of an emergency, the battery is flooded by ambient water drawn from around the water vehicle.

Abstract: The present invention relates to a method for producing a coating on a gas turbine component, in which particles at least of parts of a material to be applied as coating are accelerated by means of kinetic gas dynamic cold spraying in a spray jet onto the surface (2) of the component (1) to be coated, wherein a reactive gas is fed into the spray jet (6), so that the reactive gas reacts at least partially with the particles of the coating material when the particles impinge on the surface (2) to be coated and/or wherein the deposited layer (9) is heated locally and/or over a large area and impacted with a reactive gas, as well as a gas turbine component produced in this way.

Abstract: A method for measuring the thickness of a coating on a component section of a rotating component, wherein a heat expansion of the component section is determined by detecting a component core temperature and an actual coating thickness is produced, a device for conducting a method of this type having a temperature detecting system and having an evaluating device, as well as a production process and a coating system, are disclosed.

Abstract: A method for determining the outlet cross-section of a component including one or more turbine blades, in particular of a turbine blade twin, of a gas turbine, in which at least one closed outlet cross-section is measured between the turbine blades, and/or respective open outlet cross-sections are measured on the side of the at least one turbine blade, using a measurement device, wherein in order to determine the corresponding outlet cross-section its respective bounding walls are traversed by the measurement device along a measurement line.

Abstract: A method for producing an abradable spray coating for a component of a turbine engine by a thermal spraying process is disclosed. A process parameter pB1 is calculated according to the formula pB1=pB2+HB1?HB2?(?x·y)/z+n where pB1 is a process parameter of a spraying process that is to be conducted, pB2 is a corresponding process parameter of a previous spraying process, HB1 is a hardness of a coating that is to be applied by the spraying process to be conducted, HB2 is a hardness of a coating that was applied by the previous spraying process, ?x is a process variable related to the thermal spraying process and the previous spraying process and y, z and n are constant parameters.

Abstract: The invention relates to a method for regulating a stationary gas motor (1). In said method, a deviation of the regulated speed is calculated from a desired speed and an actual speed, a desired moment is determined as an adjustable variable from the deviation of the regulated speed by means of a speed governor, said desired moment being limited to an air ratio-limiting moment by limiting the moment, and a desired volume flow (VSL) is determined from the limited desired moment in order to define an angle (DKW1, DKW2) of the mixture throttle valve and an angle of the gas throttle valve.

Abstract: A method for automatically controlling an internal combustion engine, in which an axial displacement (s(t)) and an angle of rotation (w(t)) of a gas-exchange valve are measured during a valve stroke. A displacement deviation is computed from the displacement (s(t)) relative to a reference valve, and an angle of rotation deviation is computed from an initial value and an end value of the angle or rotation. The further operation of the internal combustion engine is set on the basis of the displacement deviation and the angle of rotation deviation.

Abstract: The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (?a, ?b) relative to their respective base inclination, wherein the angles (?a, ?b) in regard to the base inclination feature opposite signs.

Abstract: In a method for controlling the NOx concentration in the exhaust gas of an internal combustion engine in which an NOx control deviation is calculated from an actual NOx value and a desired NOx value, a control value is calculated based on the NOx control deviation via an NOx controller and by means of the control value at least one condition of the cylinder inlet flow volume of the internal combustion engine is adjusted in that, additionally, an adaption injection begin is determined in dependence on the control value of the NOx controller, and the injection begin is changed by the adaption injection begin.

Abstract: The invention relates to a clearance control system for adjusting a running clearance (L) between a rotor (12) having rotor blades (10) of a turbomachine (14), especially a gas turbine, and a casing (18) that surrounds at least sections thereof and comprises at least two segments (16a-d), the clearance control system having at least one adjusting device (20), which can be coupled to at least one segment (16a-d) of the casing (18), and by means of which the at least one segment (16a-d) can be moved radially in relation to a rotational axis (D) of the rotor (12) for adjusting the running clearance (L), wherein each segment (16a-d) of the casing (18) is coupled to at least three adjusting devices (20) of the clearance control system. The invention also relates to a turbomachine (14), especially a gas turbine, as well as to a method for adjusting a running clearance (L).

Abstract: A method for checking a blade contour of a turbomachine, in particular a gas turbine, wherein an actual contour (1; 1?) of a blade is detected, wherein a target contour of the blade is scaled and the actual contour is compared with said scaled contour (2).

Abstract: A method for monitoring a production process with regard to quality is disclosed. The method includes: a) breaking down the production process into a sequence of individual steps, defined by a sequence of control commands for a production program for carrying out the production process on a machine tool; b) generating at least one signal template per individual step of the production process from the control commands for the individual steps, each signal template corresponding to a theoretical signal curve for a parameter which may be measured upon executing the production process; c) measurement of a signal curve for at least one parameter per individual step during the execution; and d) comparison of the or each measured signal curve with the respective arithmetically generated signal template, wherein a qualitatively poor production process is determined if the measured signal curve deviates from the signal template by more than a given tolerance.

Abstract: A blade arrangement for a turbo engine, in particular a gas turbine, with a rotor and several blades fastened thereto, which are configured to be systematically different, wherein at least two adjacent blades have systematically different shrouds (12, 22) and/or inner blade platforms (11, 21).

Abstract: The present invention relates to a method for replacing an inner disk element of a blade integrated disk wherein the blade integrated disk has a plurality of recesses in the form of axial through-bores in the joining area. The method begins with filling the axial through-bores, after which the inner disk element of the blade integrated disk is separated from the remaining blade ring. Next a new inner disk element is inserted into the remaining blade ring and the new inner disk element and the remaining blade ring are joined. Finally the axial through-bores are restored.

Abstract: The invention relates to a device for producing, repairing and/or replacing a component, particularly an aircraft component, by means of a powder that can be solidified by energy radiation of an energy radiation source, characterized in that the device comprises an application unit that is designed such that the powder can be applied onto an uneven surface by means of the application unit.

Abstract: The invention at hand relates to a housing for a compressor of a gas turbine, in particular of an aircraft gas turbine, with an external housing with at least one air supply opening and an interior housing formed by at least two housing segments, with the housing segments having at least one injection nozzle to inject air suctioned in via the air supply openings into a flow channel in the area of blade tips of blades of a rotor of the compressor. In this case, the housing segment has at least one air flow channel, with the air flow channel being designed in such a way that a direct air supply to the at least one injection nozzle occurs via at least one air supply element arranged in the air supply opening of the exterior housing. The invention relates moreover to a compressor of a gas turbine as well as to a method for the manufacture of a housing segment of a compressor housing.