Abstract: A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90° before the measuring fluid exits the fluid channel at the at least one outlet.

Abstract: A combustion chamber assembly for an engine includes a wall element fixed to a combustion chamber structure and a chamber between the wall element and the structure, the chamber being supplied with air through impingement-cooling openings in the structure and connected to the combustion space by film-cooling openings in the wall element. Two cooling-air holes formed in the structure generate a cooling-air flow toward the combustion space and past the wall element. The wall element has a flow guide device for generating at least one scavenging-air flow directed between the two cooling-air holes. A sum of flow cross sections of film-cooling openings in the wall element and of the flow guide device yields a larger area than a sum of flow cross sections of all wall element impingement-cooling openings via which air is guided through the structure into the chamber and to the rear side of the wall element.

Abstract: The proposed solution relates to a combustion chamber assembly of an engine (T), in which an overrun of a spark plug is defined with a specific outer cone and a specific inner cone, and mixing air holes of a first arrangement and of at least one second arrangement that lie at least partially in a partial region of the overrun of the spark plug, said overrun being defined by the outer cone and the inner cone and extending downstream of the spark plug as far as an inner apex point (Si) of the inner cone, are formed with a flow cross section which is different from a flow cross section which the mixing air holes adjoining in the circumferential direction (U) of the respective arrangement have.

Abstract: A method of inserting a pin in a bore of an article may include first providing an article with a bore, the bore having an inside diameter. The method may then include providing a pin having a hollow body, the hollow body having a diameter with a profile with a pattern of voids. The method may then include applying an axial force on an end of the hollow body to cause the diameter of the pin to reduce in size to a point where the diameter of the pin is less than the inside diameter of the article. The method may further include aligning the pin inside of the bore of the article, and then removing the axial force on the end of the hollow body.

Abstract: A combustion chamber assembly for an engine includes one combustion chamber component of a combustion chamber structure surrounding a combustion space, and one shingle component fixed on the combustion chamber component and having a hot side facing the combustion space and a cold side facing away from the combustion space and towards the combustion chamber component. A mixing air hole formed by a through hole in the combustion chamber component and a shingle hole in the shingle component feeds mixing air into the combustion space. The through hole defines an inlet opening for mixing air on an outer side of the combustion chamber component, and, on the hot side, the shingle hole defines an outlet opening for mixing air flowing in via the inlet opening. The through hole is provided eccentrically with respect to the shingle hole, based on a central point of the outlet opening.

Abstract: Void structures, systems and devices with void structures, and methods of fabricating void structures are disclosed. A void structure is disclosed with a repeating elongated-aperture pattern designed to provide negative Poisson's Ratio behavior under macroscopic stress and strain loading. The pattern can include horizontal and vertical elliptically shaped apertures that are arranged on horizontal and vertical lines in a way that the lines are equally spaced in both dimensions. The centers of each aperture is on a crossing point of two of the lines. The vertical and horizontal elliptically shaped apertures alternate on the vertical and horizontal lines such that any vertical aperture is surrounded by horizontal apertures along the lines (and vice versa), and the next vertical apertures are found on both diagonals. The voids can also act as cooling and/or damping holes and, due to their arrangement, also as stress reduction features.

Abstract: A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is ?50°.

Abstract: A combustion chamber assembly for an engine, with a tile component fixed to a combustion chamber component and having a hot side facing a combustion space and a cold side facing away from the combustion space and facing towards the combustion chamber component, wherein the tile component on the cold side has at least four fixing elements each arranged eccentrically on the tile component for fixing the tile component to the combustion chamber component. The four base bodies are here oriented with their respective at least one side passage opening towards a reference point lying on a center line of the tile component, so that a respective cavity of the respective base body is open in the direction of the reference point.

Abstract: The present invention relates, in particular, to an engine component, having at least one cooling duct, which extends from an inlet opening on a first side of the engine component to an outlet opening on a second side of the engine component through the engine component. A second, inner duct wall of the cooling duct has a recess relative to an opposite first, outer duct wall in a region of the cooling duct situated between the inlet opening and the outlet opening, said recess being of V-shaped design in a cross-sectional view through the cooling duct and in a direction of view along a direction of extent of the cooling duct.

Abstract: The proposed solution relates to a combustion chamber assembly of an engine (T), in which an overrun of a spark plug is defined with a specific outer cone and a specific inner cone, and mixing air holes of a first arrangement and of at least one second arrangement that lie at least partially in a partial region of the overrun of the spark plug, said overrun being defined by the outer cone and the inner cone and extending downstream of the spark plug as far as an inner apex point (Si) of the inner cone, are formed with a flow cross section which is different from a flow cross section which the mixing air holes adjoining in the circumferential direction (U) of the respective arrangement have.

Abstract: A combustion chamber assembly for an engine includes a wall element fixed to a combustion chamber structure and a chamber between the wall element and the structure, the chamber being supplied with air through impingement-cooling openings in the structure and connected to the combustion space by film-cooling openings in the wall element. Two cooling-air holes formed in the structure generate a cooling-air flow toward the combustion space and past the wall element. The wall element has a flow guide device for generating at least one scavenging-air flow directed between the two cooling-air holes. A sum of flow cross sections of film-cooling openings in the wall element and of the flow guide device yields a larger area than a sum of flow cross sections of all wall element impingement-cooling openings via which air is guided through the structure into the chamber and to the rear side of the wall element.

Abstract: A measuring device with at least one fluid channel for conveying a measuring fluid, wherein the fluid channel includes at least one inlet for the entry of the measuring fluid into the fluid channel and at least one outlet for the exit of the measuring fluid from the fluid channel. The fluid channel comprises includes a diamond-shaped cross-section and includes a course from the at least one inlet to the at least one outlet over which the measuring fluid entering the fluid channel is deflected by at least 90° before the measuring fluid exits the fluid channel at the at least one outlet.

Abstract: A wall of a structural component to be cooled by means of cooling air with at least one cooling air channel, which at least in its outflow area is arranged so as to be inclined at an angle with respect to the wall inclined, penetrating the wall from the side at which the cooling air is supplied to the thermally loaded side, characterized in that the cooling air channel has a tubular extension on the side where the cooling air is supplied, wherein the tubular extension is arranged at an angle to the surface of the wall and is supported by means of a rib with respect the surface of the wall, and in particular to an inner gas turbine combustion chamber wall with effusion holes.

Abstract: A device for cooling a wall of a component of a gas turbine, where a flow passes parallel to the wall, having at least one inflow duct provided in the wall that issues into a recess of the wall for supplying cooling air, wherein a center axis of the inflow duct is aligned to an impact wall of double-convex design inside the recess.

Abstract: A combustion chamber assembly group includes a nozzle providing a fuel-air mixture at a nozzle exit opening. An end of a fuel guiding channel is bordered at the nozzle exit opening by a flow-off edge located radially outside, and an air guiding element of an air guiding channel of the nozzle located radially outside projects with respect to this flow-off edge in the axial direction with respect to a nozzle longitudinal axis such that: a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and tangentially to the axially projecting air guiding element, and/or a reference angle present between the nozzle longitudinal axis and a straight boundary line extending through a point at the flow-off edge and a point of the air guiding element that projects maximally beyond the flow-off edge in the axial direction is ?50°.

Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile.

Abstract: A combustion chamber of a gas turbine, with at least one shingle that including a plate-shaped shingle body that has a circumferential shingle edge which is raised from the side that is facing away from the combustion chamber interior space, and which abuts against a combustion chamber wall in the mounted state of the shingle, wherein the shingle body is provided with an arrangement of effusion cooling holes, and the combustion chamber wall is provided with an arrangement of impingement cooling holes in the area of the shingle, wherein the arrangement of impingement cooling holes has a lateral distance to the shingle edge that is between 1.5 and 2 times the distance of the surface of the combustion chamber wall to the surface of the shingle body, and that the distance of the arrangement of impingement cooling holes is between 1.1 and 3 times the lateral distance in the corner areas of the shingle.

Abstract: The present invention relates to a gas-turbine combustion chamber having a head plate as well as an outer and an inner combustion chamber wall, wherein the combustion chamber is formed by segments or partial segments manufactured in one piece by means of a DLD method and welded to one another.

Abstract: The present invention relates to a gas-turbine combustion chamber having a combustion chamber wall, to which combustion chamber tiles are fastened by means of bolts, where in the bolt fastening area in the combustion chamber wall at least one impingement cooling hole is provided, the center axis of which is inclined to the center axis of the bolt and intersects a transition area between the bolt and the combustion chamber tile.

Abstract: A wall of a structural component to be cooled by means of cooling air with at least one cooling air channel, which at least in its outflow area is arranged so as to be inclined at an angle with respect to the wall inclined, penetrating the wall from the side at which the cooling air is supplied to the thermally loaded side, characterized in that the cooling air channel has a tubular extension on the side where the cooling air is supplied, wherein the tubular extension is arranged at an angle to the surface of the wall and is supported by means of a rib with respect the surface of the wall, and in particular to an inner gas turbine combustion chamber wall with effusion holes.