Abstract: The present invention relates to an aircraft gas turbine comprising a thrust-reverser device that is arranged at the rear area of an engine cowling and that has multiple cascade elements which are distributed at the circumference and which divert a stream, characterized in that the cascade elements are mounted in a displaceable manner, in that on both sides of each cascade element at least one gear rack is formed that can be displaced via a respective cog wheel which is coupled to a driving device, and in that each cascade element is connected to a rear area of the engine cowling via a coupling element for the purpose of displacing the engine cowling in the axial direction.

Abstract: It is provided a mixer for an engine, that for the mixing of fluid flows from a primary flow channel and a secondary flow channel of the engine, respectively has multiple first and second guide elements that alternate along a circumferential direction and extend along a central axis, wherein the first guide elements are formed in a diffusor-like manner with at least one radially outwardly extending section, and the second guide elements are formed in a nozzle-like manner with at least one radially inwardly extending section, and the mixer is made of a composite material with at least two separate material layers. The at least two material layers are arranged with their edges along the central axis in an overlapping manner and/or edge to edge, and namely in an area of the mixer in which the first and second guide elements are provided.

Abstract: An air guide element of an aircraft gas turbine, including an external housing that is provided with an inflow opening, as well as with a flow channel that is arranged inside the housing, characterized in that a tubular intermediate element that is made of an elastic material is arranged inside the inflow opening, connecting the inflow opening to the flow channel in a sealing and position-adjusting manner.

Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.

Abstract: A gas turbine engine has a core engine and a nacelle having a cowl translatable along the axis of the engine from a stowed position to a deployed position, A thrust reverser cascade extends circumferentially about the engine axis. To obviate the need for additional blanking cascades the cowl has a forwardly extending tongue that in the deployed position of the cowl is at the same axial position as the thrust reverser cascade.

Abstract: A bypass duct has a support unit comprising a pair of aerofoils arranged as an “A” frame. A bleed duct assembly is provided on the radially inner wall of the bypass duct annulus and the aerofoils project from the surface and extend across the annulus between the inner wall and an outer wall of the annulus. The aerofoils lean at an acute angle to the surface with the first flank facing toward the inner wall and adjoining a bleed duct opening. The bleed duct having a bleed duct passage and a submerged scoop.

Abstract: A mixer assembly group for a turbofan engine, having a primary flow channel extending along a central axis of the turbofan engine and a secondary flow channel. The mixer assembly group includes a mixer for guiding a first fluid flow from the primary flow channel and a second fluid flow from the secondary flow channel in the direction of an exhaust of the turbofan engine, as well as for intermixing the first and second fluid flows, and a connection appliance, which has at least one connection component that is fixated at the mixer and by means of which the mixer assembly group is to be fixated at two different first and second engine components of the turbofan engine, with are subject to operating temperatures of different heights during operation of the turbofan engine.

Abstract: A device of a turbomachine actuates a setting device to vary a flow cross-section of a flow channel of the turbomachine passable by a fluid flow. The device includes a displacement mechanism having an adjustable actuation appliance and couplable with the setting device, and a drive device for displacing the actuation appliance. The displacement mechanism has a centrifugal force appliance displaceable between a basic position and a maximally displaced working position depending on a number of revolutions of the drive device, wherein the actuation appliance is displaceable depending on the position of the centrifugal force appliance with respect to the drive device. A reset device applies a force to the centrifugal force appliance by which the centrifugal force appliance is pressed in the direction of its basic position.

Abstract: A blocker door for a gas turbine engine thrust reverser having a tray with a base and sidewalls extending about the base to define a volume, the volume being closed by a cover that extends beyond the periphery of the tray. The extension of the cover beyond the periphery provides a sealing feature.

Abstract: An aircraft gas-turbine engine has an engine cowling-nacelle which surrounds a core engine in a tubular way, characterized in that at least one inflow-side part of the engine cowling-nacelle is telescopically movable against the flow direction.

Abstract: A turbomachine having a wall that extends circumferentially to a central axis of the turbomachine at least in certain areas, and having at least one insert device that can be connected in a releasable manner to a wall in the area of a recess which is arranged inside the wall. The insert device has a connection device by means of which the insert device can be brought into operative connection with a connection device of the wall. The connection device of the insert device has a projection that extends in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device, and that in the mounted state of the insert device meshes in a groove of the connection device of the wall. The connection device of the wall has a projection that extends in the radial direction of the turbomachine at least in certain areas in the mounted state of the insert device, and that, in the mounted state of the insert device, meshes in a groove of the connection device of the insert device.

Abstract: An aircraft gas turbine having a core engine casing for a core engine, said core engine casing including at least a compressor area, a combustion chamber area and a turbine area, wherein the core engine casing is provided on its outer wall with several cooling-air tubes which are designed in one piece with said outer wall and extend in the axial direction relative to an engine axis.

Abstract: The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling whose rear area can be moved in the axial direction of the engine from a closed forward-thrust position into a rearward moved thrust-reversing position in which a free, substantially annular space to a front and fixed area of the engine cowling is present, where on the engine cowling guide rails are arranged, inside which mounting elements can be moved by means of rolling or sliding elements, with which mounting elements the rear area of the engine cowling is mounted, characterized in that the guide rails have an oval and C-shaped cross-section, provided on a longitudinal side with a slot-like opening, and are mounted using mounting projections arranged centrally and opposite to one another and designed in one piece with the C-shaped cross-section.

Abstract: A guide vane of a gas turbine engine, in particular of an aircraft engine, which has a pressure-side wall, a suction-side wall, a guide vane root, a guide vane tip, a guide vane leading edge area that is impinged by a cooling air flow of a cooling system, a guide vane trailing edge area that is facing away from the guide vane leading edge area, and at least one channel for conducting a fluid to be cooled arranged in an internal space of the guide vane. At that, during operation of the gas turbine engine, a first part of the cooling air flow flows around a pressure-side wall, and a second part of the cooling air flow flows around the suction-side wall, and a third part of the cooling air flow flows through the internal space including the channel. What is further suggested is a gas turbine engine with at least one such static guide vane.

Abstract: An engine cowling of an aircraft gas turbine with a front area and a rear area that is displaceable in the axial direction, characterized in that the rear area is mounted and supported by means of multiple length-adjustable thrust reversal actuators that are arranged at an angle to one another.

Abstract: The invention relates to an engine cowling of an aircraft gas turbine which has a rear area that comprises at least two doors that are arranged at the bottom area of the rear area of the engine cowling and are to be opened by means of overhead hinges, wherein the hinges are arranged so as to be tilted with respect to the engine axis.

Abstract: An engine cowling of an aircraft gas-turbine engine with a core engine and a bypass duct surrounding the latter, with a front cowling enclosing the bypass duct and a rear cowling movable in the axial direction, and with stator vanes arranged in the bypass duct, where recesses for removing fluid from the bypass duct are provided in the area of the stator vanes on the inside of the front cowling, where the fluid discharged through the recesses is routed by means of flow ducts through the front cowling, brought into contact with at least one heat exchanger, and subsequently discharged to the environment.

Abstract: An engine cowling of an aircraft gas-turbine engine with a thrust-reversing device, with a core engine and a bypass duct surrounding the latter, and with a front cowling enclosing the bypass duct and a rear cowling movable in the axial direction, as well as with cascade elements arranged over the circumference which can be placed by a substantially axial movement into an intermediate space resulting from a movement of the rear cowling relative to the front cowling, characterized in that the cascade elements are connected directly to the rear cowling, that the rear cowling has a rounded outer leading edge and that the cascade element has at its rear area a flow-guiding element, in front of which several thrust-reversing stator vanes are arranged and behind which at least one flow stator vane is arranged whose curvature shape matches the rounding of the outer leading edge of the rear cowling.

Abstract: An aircraft gas turbine thrust-reversing device has an engine cowling, the rear area of which is displaceable in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular space to a front and stationary area of the engine cowling. The rear area of the engine cowling is coupled to deflecting elements and blocker doors, which in the forward thrust position are arranged completely inside the front area of the engine cowling. A drive element is provided between the front area and the rear area, which effects the axial displacement of the rear area. The drive element is a two-stage drive element, effecting in a first stage an axial displacement by an axial partial displacement path, and in a second stage an axial displacement by the full axial displacement path.

Abstract: The present invention relates to an engine casing of an aircraft gas turbine having a radially inner honeycomb-structured layer arranged on the engine casing in the flow direction upstream of a fan in the area of an inflow-side air inlet, characterized in that sound-absorbing elements are arranged radially outside at least one axial section of the honeycomb-structured layer, said elements extending in the axial direction and being arranged annularly next to one another in the circumferential direction.