Abstract: A structural unit for arrangement at a hydraulic fluid tank of a jet engine that is embodied with an outlet appliance for draining hydraulic fluid. When the structural unit is arranged at a hydraulic fluid tank, the outlet appliance has an outlet opening that is facing towards the hydraulic fluid tank. The structural unit is further embodied with at least one measuring appliance, by means of which a filling level of a hydraulic fluid that is present inside the hydraulic fluid tank can be determined when the structural unit is arranged at a hydraulic fluid tank. A fixture appliance is provided for fixedly attaching the structural unit at a hydraulic fluid tank.

Abstract: A gas turbine engine comprising a gearbox, the gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier, each planet gear being rotatably mounted in the carrier by at least one bearing, the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear, the sun gear, the planet gears and the annulus gear comprising gear teeth, the annulus gear having a length in the axial direction and an axially forward end and an axially rearward end and wherein the annulus gear is resiliently mounted to a supporting structure at both its axially forward and axially rearward ends.

Abstract: A rotor for an engine is provided. The rotor comprising a rotor base part that has fastening grooves for rotor blades that are arranged in succession around a rotational axis along a circumferential direction, multiple rotor blades that are respectively supported in a form-fit manner inside a corresponding fastening groove by means of a blade root, and at least one securing element for the axial securing—with respect to a rotational axis of at least one of the rotor blades at the rotor base part. The at least one securing element has two edges that are arranged at a radial distance to one another and through which the securing element is supported in a form-fit manner at the rotor base part, on the one hand, and, on the other hand, at the at least one rotor blade.

Abstract: An investment casting pattern including: a consumable body formed of: a first body portion; and a second body portion; and a fastener arranged to form an interface between the first body portion and the second body portion, and to locate the first body portion relative to the second body portion, wherein the fastener is formed of a different material than the first body portion and the second body portion.

Abstract: A geared turbofan engine with a sun shaft driving a sun gear of planetary gearbox. The sun shaft having a front section proximal to the gearbox and a rear section distal from the gearbox. The outer diameter of the front section of the sun shaft is smaller than the outer diameter of the rear section of the sun shaft. The front section of the sun shaft having between two and four undulant sections, wherein each undulant section having at least one axial part extending in axial direction of the sun shaft and two diaphragm parts on either side of the at least one axial part extending in radial direction outward, the at least one axial part of the undulant section having an inner diameter smaller than the outer diameter of the front section of the sun shaft.

Abstract: Methods for manufacturing a tandem guide vane segment that includes an outer platform, a front guide vane, and a rear guide vane, wherein the front guide vane and the rear guide vane are arranged in a firmly fixated manner with respect to one another. One method includes manufacturing an integral front segment section that includes the front guide vane and a front section of the outer platform, manufacturing an integral rear segment section that includes the rear guide vane and a rear section of the outer platform, and connecting the two segment sections to each other.

Abstract: A gas turbine engine, in particular an aircraft engine is provided. The gas turbine engine including a geared turbofan arrangement, a propulsive fan and a planetary gearbox being driveably connected with a first shaft on the output side of the planetary gearbox and a second shaft on the input side of the planetary gearbox. The propulsive fan is supported through a front load path and a rear load path, the front load path including a first bearing between the first shaft and a sun gear, the rear load path including a second bearing between the second shaft and a fixed structure of the gas turbine engine. The first shaft including a first portion of the shaft as torque carrying part, wherein the torque carrying part including a torque carrying coupling being connected to the first shaft and to a carrier of the planetary gearbox.

Abstract: An engine cowling includes at least one cowling part, at least one door element and at least one hinge. The hinge connects the door element to the first cowling part in an openable and closable manner. The hinge can be adjusted in a three-dimensional manner in a first direction, a second direction and a third direction in order to change a relative position of the door element with respect to the first cowling part.

Abstract: A monitoring system for a multiple-walled fluid system with a first walled region including a flowing or stagnant fluid and at least one second walled region at least partially surrounding the first walled region. The first walled region and the at least one second walled region forming the multiple-walled fluid system, the first walled region being in fluid communication with the at least one second walled region, the at least one second walled region also being in fluid communication with the ambient environment. A data processing device for monitoring at least one pressure difference between a pressure in at least one a control volume and at least one second pressure in the at least one second walled region, a first control volume in fluid connection with the first walled region and the ambient environment. The at least one pressure difference indicating the status of the multiple-walled fluid system.

Abstract: A guide vane assembly with at least one guide vane row and a housing for the at least one guide vane row that extends along a circumferential direction about a central axis, wherein the at least one guide vane row includes multiple guide vanes that are respectively mounted at the housing in an adjustable manner by means of an adjusting appliance of the guide vane assembly. The adjusting appliance includes at least one adjusting element for adjusting the guide vanes that is arranged at a radial distance to an outer side of the housing with respect to the central axis, and a compensation device is provided, by means of which a radial distance of the adjusting element to the outer side of the housing is predetermined, and the different thermal expansions of the adjusting element and of the housing are at least partially compensated.

Abstract: A gas turbine engine includes a spool which rotates in use, a static structure and an air bearing, the air bearing being provided at an interface between the spool and the static structure.

Abstract: A method for manufacturing at least one part of an engine component by means of a blank from an intumescent material, which contains at least one fibrous matrix of organic and/or inorganic fibers and an intumescent substance, is provided. The blank is created from the intumescent material with a three-dimensional structure that is already adjusted with respect to its contours to the contours of the part of the engine component to be manufactured and the blank comprising the three-dimensional structure is impregnated through a hardening resin, and is connected, prior to or after the impregnation, to at least one support material that is also already adjusted to the contours of the part to be manufactured and at least partially forms the engine component together with the blank connected thereto.

Abstract: A guide vane assembly, with at least one guide vane row and a housing for the at least one guide vane row that extends along a circumferential direction about a central axis. The at least one guide vane row comprises multiple guide vanes that are respectively mounted at the housing in an adjustable manner by means of an adjusting appliance of the guide vane assembly. The adjusting appliance comprises at least one adjusting element for adjusting the guide vanes that is arranged at a radial distance to an outer side of the housing with respect to the central axis. A compensation device is provided, via which a radial distance of the adjusting element to the outer side of the housing is predetermined, and the different thermal expansions of the adjusting element and of the housing are at least partially compensated for the purpose of maintaining these distances.

Abstract: A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.

Abstract: A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and additional, sacrificial elements for supporting interim elements; b) on a base plate, depositing multiple layers of a powder including a material from which the pre-component will be manufactured; c) sintering the powder to form the pre-component to the defined geometry; d) removing at least some of the sacrificial elements from the pre-component; e) subjecting the remaining pre-component from step d) to a HIP step; and f) removing remaining sacrificial elements from the pre-component product of step e) to provide a component to the defined component geometry. In the definition of the pre-component geometry, the interim elements differ from the corresponding final shape elements in the defined component geometry such that during the HIP step, the interim shape elements adjust to form final shape elements in the defined component geometry.

Abstract: A diffuser component for a gas turbine is provided, where a fluid flow in the direction of a combustion chamber of the gas turbine can be slowed down by the diffuser component, and a flow cross-section of the diffuser component, which is defined by a diffuser wall is widened to do so. The diffuser wall is at least locally braced, in that at least one stiffening element with a lattice-type structure is provided on the diffuser wall.

Abstract: A device for adjusting a gap between the housing of an impeller and the impeller in a radial compressor of a turbomachine is provided. The device comprises at least one mechanical setting device by means of which the housing of the impeller can be axially adjusted in a targeted manner for the purpose of adjusting the gap, wherein the at least one setting device can be actuated via an adjusting ring, and a transmission of a force and/or a torsional moment from the adjusting ring can be effected via at least one adjustment lever device, in particular a thread lever, or a tilting lever.

Abstract: A jet engine with a bearing chamber, a sealing chamber, a de-aeration chamber and a bearing chamber support, the support delimiting the bearing chamber comprising at least one bearing appliance in certain areas. The bearing chamber is separated from the sealing chamber via a sealing appliance, with the sealing chamber being separated via a further sealing appliance from the de-aeration chamber that is arranged at the side of the sealing chamber facing away from the bearing chamber. The sealing chamber is connected to a sealing air conduit, by which the bearing chamber can be supplied with a sealing air volume flow. The de-aeration chamber is connected to a de-airing appliance via which a volume flow can be discharged from the de-aeration chamber into a core flow channel of the jet engine. The de-airing appliance is embodied as at least one air extraction duct with a tubular flow cross-section.

Abstract: A combustion chamber of a gas turbine with a combustion chamber wall to which effusion tiles are fastened which adjoin one another while forming a rim gap, with a seal being arranged in the area of said rim gap, characterized in that the effusion tiles at their rim facing the combustion chamber wall are provided with a bevel in order to form a sealing space, that a seal having a V-shaped cross-section is placed inside the sealing space and that the combustion chamber wall is provided with at least one recess to supply cooling air through the combustion chamber wall to that side of the seal facing the combustion chamber wall.

Abstract: An adaptive aircraft engine including a first, inner bypass duct inside a core engine of the aircraft engine and a second, outer bypass duct at least partially surrounding the first bypass duct, and adaption means, in particular adjustable nozzles for altering a flowed-through cross-section of the core engine with the first bypass duct and for altering the flowed-through cross-section of the second bypass duct depending on the flying speed. An aircraft having at least one adaptive aircraft engine is also provided.