Abstract: Computer implemented method for determining boundary thermal resistance data (Rbl) of a boundary layer (15), comprising the following steps: obtaining first temperature data (T1) from a first temperature sensor (13), which is arranged at a first pipe section (S1); obtaining second temperature data (T2) from a second temperature sensor (14), which is arranged at a second pipe section (S2); wherein the first temperature sensor (13) and the second temperature sensor (14) are non-invasive temperature sensors; providing process condition data (P); determining boundary thermal resistance data (Rbl) of a boundary layer (15) of the fluid (11) next to an inner surface (16) of the wall of the pipe (12) based on the process condition data (P) and/or based on the first temperature data (T1) and/or the second temperature data (T2).

Abstract: A computer implemented method for determining boundary thermal resistance data of a boundary layer includes obtaining first temperature data from a first temperature sensor, which is arranged at a first pipe section; obtaining second temperature data from a second temperature sensor, which is arranged at a second pipe section, wherein the first temperature sensor is a non-invasive temperature sensor and the second temperature sensor is an invasive temperature sensor; providing process condition data; determining boundary thermal resistance data of a boundary layer of the fluid next to an inner wall of the pipe based on the process condition data.

Abstract: A method for validating an invasive temperature measurement system includes providing a first temperature data of the invasive temperature measurement system of a medium, the medium surrounded by a vessel wall enclosing the medium; providing a second temperature data of a non-invasive temperature measurement system, the non-invasive temperature measurement system thermally contacting an outside surface of the vessel wall enclosing the medium; determining a temperature of the medium based on the second temperature data medium properties and properties of the vessel wall; and comparing the first temperature data with the determined temperature of the medium to validate the invasive temperature measurement system.

Abstract: A temperature sensor assembly configured to be coupled thermally to a vessel wall for determining a temperature of a surface of the vessel wall is provided, the assembly includes: a first single-branched thermal conduction path, between the surface of the vessel wall and an environment of the temperature sensor assembly, comprising a temperature measurement sensor, configured to be thermally coupled to a first site of the surface of the vessel wall resulting in a first thermal resistance; and a second single-branched thermal conduction path, between a second site of the surface of the vessel wall and an environment of the temperature sensor assembly, comprising a reference temperature sensor, configured to be thermally coupled to the surface of the vessel wall resulting in a second thermal resistance.

Abstract: A positioner drive for controlling a valve positioner with pneumatic output is configured to be mechanically coupled to a valve of the valve positioner with pneumatic output for controlling the valve positioner with pneumatic output.

Abstract: A temperature-measuring device for determining the temperature of a surface or a medium by utilizing the temperature of the surface enclosing the medium includes at least one measuring sensor and at least one reference sensor as well as a value processing device, which is connected to the measuring sensor via a first connection line and which is connected to the reference sensor via a second connection line, wherein of both connection lines at least the first connection line is partly realized as a mineral-insulated sheathed cable providing the measuring sensor, wherein both connection lines comprise a flexible cable connected to the value processing means.

Abstract: A high lift system for an aircraft includes at least one lift flap arranged on a wing forming a gap between a leading edge of the wing and a trailing edge of the lift flap in an extended position of the lift flap, and at least one flap adjustment mechanism for moving the lift flap between a retracted and at least one extended position relative to the wing. The wing includes a depression with a leading depression edge for accommodating the lift flap in a retracted position, and arranged in such an area of the wing that a correspondingly formed trailing edge region of the lift flap includes a curvature, by which the gap between the leading edge of the wing and trailing edge of the lift flap is convergent. A convergent and improved gap increases the efficiency of a high lift system without any active or movable means.

Abstract: An aerodynamic fairing body for an aircraft, a corresponding aircraft and a corresponding method of manufacture for an aerodynamic fairing body are described. The fairing body is configured so as to accommodate a flap adjustment mechanism. Further, the fairing body is configured so as to be arranged at a predetermined distance from an engine of the aircraft, which produces a blast which varies depending on the flight phase. Furthermore, the fairing body is configured so as to be varied in shape in such a way that the fairing body is located outside the blast of the engine permanently. In other words, the fairing body can be varied in shape in such a way that it is located outside the engine blast in any flight phase of the aircraft.

Abstract: A process for manufacturing a ceramic implant with a surface which forms a permanent bonding to bone cell tissues, the surface providing improved osseointegration, the process comprising the step of:—a pretreatment of the ceramic material with the surface wherein said surface of the ceramic material is exposed to a conditioning plasma, which is produced by means of direct current (DC) or alternating current (AC), such as high or radio frequency (HF, RF), or microwaves (MW) at a low pressure, followed by a second step;—a treatment with a reactive plasma in which an organic compound is added to the plasma for the at least partial application of an organic phase to said surface wherein the organic compound is selected from the group consisting of aliphatic amines, cyclic amines, unsaturated and aromatic amines as well as combinations thereof.

Abstract: An implant having a base body, comprised either entirely or in part of a biocorrodible metallic material wherein at least the parts of the base body having the biocorrodible metallic material are at least partially covered with a coating of a crosslinked CFx layer that is nonpolymerized and has an F/C ratio in the range of 0.5 to 1.5.

Abstract: A process for manufacturing a ceramic implant with a surface which forms a permanent bonding to bone cell tissues, the surface providing improved osseointegration, the process comprising the step of:—a pretreatment of the ceramic material with the surface wherein said surface of the ceramic material is exposed to a conditioning plasma, which is produced by means of direct current (DC) or alternating current (AC), such as high or radio frequency (HF, RF), or microwaves (MW) at a low pressure, followed by a second step;—a treatment with a reactive plasma in which an organic compound is added to the plasma for the at least partial application of an organic phase to said surface wherein the organic compound is selected from the group consisting of aliphatic amines, cyclic amines, unsaturated and aromatic amines as well as combinations thereof.

Abstract: An aerodynamic fairing body for an aircraft, a corresponding aircraft and a corresponding method of manufacture for an aerodynamic fairing body are described. The fairing body is configured so as to accommodate a flap adjustment mechanism. Further, the fairing body is configured so as to be arranged at a predetermined distance from an engine of the aircraft, which produces a blast which varies depending on the flight phase. Furthermore, the fairing body is configured so as to be varied in shape in such a way that the fairing body is located outside the blast of the engine permanently. In other words, the fairing body can be varied in shape in such a way that it is located outside the engine blast in any flight phase of the aircraft.

Abstract: A high lift system is provided for an aircraft. The high lift system includes, but is not limited to a lift flap arranged on a wing and coupled to the wing so as to be movable relative to the wing, between a retracted position and at least one extended position. In the retracted position the lift flap rests against the wing, and in an extended position forms an air gap to the wing. The lift flap directed towards its trailing edge comprises at least one region of variable curvature, which region in an extended position of the lift flap extends towards the wing.

Abstract: The invention relates to a method for coating surfaces with micro- and nanoparticles, the micro- and nanoparticles being chemically bonded to the surface, comprising the steps of pre-treatment of the surface with a plasma method, simultaneous or subsequent application of the micro- and nanoparticles to the surface, and subsequent fixation of the micro and nanoparticles on the surface using a plasma method, characterized in that the fixation of the micro- and nanoparticles takes place with the aid of anisothermal plasmas, the median electrical energy of which lies in the range of the bond dissociation energy of the micro- and nanoparticles, thus allowing the strength of the chemical bond between the surface and the micro- and nanoparticles to be variably set.

Abstract: A wing arrangement includes, but is not limited to an adjustable flap, which is adjustable between a retracted position and at least one extended position, has at least one fairing element for covering a flap adjustment mechanism and at least one cover element. The fairing element extends downstream at least as far as the flap and has, in a surface facing the flap, a cutout which correlates with an intended adjustment movement of the flap. The cover element is movably arranged with respect to the fairing element and adapted such to cover the cutout in the fairing element in the retracted position of the flap and expose at least part of said cutout in an extended position.

Abstract: A wing arrangement includes, but is not limited to an adjustable flap, which is adjustable between a retracted position and at least one extended position, has at least one fairing element for covering a flap adjustment mechanism and at least one cover element. The fairing element extends downstream at least as far as the flap and has, in a surface facing the flap, a cutout which correlates with an intended adjustment movement of the flap. The cover element is movably arranged with respect to the fairing element and adapted such to cover the cutout in the fairing element in the retracted position of the flap and expose at least part of said cutout in an extended position.

Abstract: A high lift system is provided for an aircraft. The high lift system includes, but is not limited to a lift flap arranged on a wing and coupled to the wing so as to be movable relative to the wing, between a retracted position and at least one extended position. In the retracted position the lift flap rests against the wing, and in an extended position forms an air gap to the wing. The lift flap directed towards its trailing edge comprises at least one region of variable curvature, which region in an extended position of the lift flap extends towards the wing.

Abstract: The invention relates to a method for coating surfaces with micro- and nanoparticles, the micro- and nanoparticles being chemically bonded to the surface, comprising the steps of pre-treatment of the surface with a plasma method, simultaneous or subsequent application of the micro- and nanoparticles to the surface, and subsequent fixation of the micro and nanoparticles on the surface using a plasma method, characterized in that the fixation of the micro- and nanoparticles takes place with the aid of anisothermal plasmas, the median electrical energy of which lies in the range of the bond dissociation energy of the micro- and nanoparticles, thus allowing the strength of the chemical bond between the surface and the micro- and nanoparticles to be variably set.

Abstract: An implant having a base body, comprised either entirely or in part of a biocorrodible metallic material wherein at least the parts of the base body having the biocorrodible metallic material are at least partially covered with a coating of a crosslinked CFx layer with an F/C ratio in the range of 0.5 to 1.5.