Abstract: Embodiments of the invention are shown in the figures, where a nacelle cowling structure for a turbomachine having a bypass duct defining a path for an airflow is provided, the nacelle cowling structure including: an outer layer defining an external surface of the nacelle cowling structure, an inner layer defining a surface of the bypass duct, a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream the front mounting area with respect to the bypass duct flow path, wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with acoustic material.

Abstract: Embodiments of the invention are shown in the figures, where a nacelle cowling structure for a turbomachine having a bypass duct defining a path for an airflow is provided, the nacelle cowling structure including: an outer layer defining an external surface of the nacelle cowling structure, an inner layer defining a surface of the bypass duct, a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream the front mounting area with respect to the bypass duct flow path, wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with acoustic material.

Abstract: A gas turbine engine including an engine core and including a bypass channel of an aircraft is described. The bypass channel radially surrounds the engine core at least in part. At least one core shaft extending in the axial direction is provided, which shaft is operatively connected, by means of a drive train, to a core accessory gearbox arranged between the engine core and the bypass channel, and to an aircraft accessory gearbox. The aircraft accessory gearbox is arranged radially outside the bypass channel. The drive train extends substantially in the radial direction between the core shaft and the aircraft accessory gearbox. The drive train has an angle drive between a radial shaft and the core shaft. Furthermore, the drive train comprises another angle drive between the radial shaft and the core accessory gearbox and an additional angle drive between the radial shaft and the aircraft accessory gearbox.

Abstract: A gas turbine engine for an aircraft comprising an engine core and including a bypass channel which radially surrounds the engine core at least in part is described. A core shaft is operatively connected to an engine accessory gearbox, which is arranged between the engine core and the bypass channel, by means of a radial shaft of a drive train. An electric machine is provided which is designed to start the gas turbine engine during motor operation and to generate electrical energy during alternator operation. The electric machine is arranged coaxially with the core shaft and connected thereto for conjoint rotation. Alternatively, the electric machine can be arranged radially outside the bypass channel and can be operatively connected to the core shaft by means of the radial shaft, wherein a rotor of the electric machine is arranged coaxially with the radial shaft and connected thereto for conjoint rotation.

Abstract: A ventilation device for controlling an air flow through at least one air inlet into an interior space of a gas turbine engine, comprises: at least one actuable closure device for the at least one air inlet, which has an open position for exposing the air inlet and can be transferred by actuation into a closed position for closing the air inlet; and a fire extinguishing device having an extinguishing agent arranged in a reservoir, wherein the fire extinguishing device is connected or can be connected to the interior space and the closure device in such a way that activation of the fire extinguishing device both leads to admission of extinguishing agent from the reservoir into the interior space and brings about actuation of the closure device to transfer the closure device into the closed position.

Abstract: An aircraft with a jet engine that has a radially outer engine cowling and an auxiliary gear appliance that has multiple auxiliary devices and that can be driven by a shaft that is in operative connection with an engine shaft that rotates about a central axis. The auxiliary gear appliance is arranged in the radial direction of the jet engine at least partially outside the outer engine cowling of the jet engine.

Abstract: A jet engine with a linking device for linking the jet engine at an element of an aircraft optionally in a first mounting position and at least one second mounting position, and with at least one operating equipment appliance that has a first fluid area and a second fluid area. In the first mounting position, the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality. In the second mounting position, the fluid areas are assigned to the respectively other functionality. What is further described is an aircraft with at least one such jet engine.

Abstract: A device for carrying out a chemical reaction by a continuous method has a reactor with at least two reactor sections which define a direction of flow. The reactor has plug flow properties along the direction of flow. A recirculation line is present to withdraw a partial flow from the reactor at a first point and return it to the reactor at a second point located above the first point in the direction of flow. Means are provided which prevent a temperature increase in the reactor over a predetermined temperature range, for example change of more than approximately 50 K.

Abstract: A heat-exchanger device for an aircraft engine, having a fuel-oil heat exchanger for exchanging heat between fuel and oil, and a housing with an air inlet and an air outlet, wherein the fuel-oil heat exchanger is arranged at least partially within the housing such that air flowing from the air inlet to the air outlet can flow over or around the fuel-oil heat exchanger. The invention further relates to a method for operating an aircraft engine.

Abstract: A ventilation device for controlling an air flow through at least one air inlet into an interior space of a gas turbine engine, comprises: at least one actuable closure device for the at least one air inlet, which has an open position for exposing the air inlet and can be transferred by actuation into a closed position for closing the air inlet; and a fire extinguishing device having an extinguishing agent arranged in a reservoir, wherein the fire extinguishing device is connected or can be connected to the interior space and the closure device in such a way that activation of the fire extinguishing device both leads to admission of extinguishing agent from the reservoir into the interior space and brings about actuation of the closure device to transfer the closure device into the closed position.

Abstract: A heat-exchanger device for an aircraft engine, having a fuel-oil heat exchanger for exchanging heat between fuel and oil, and a housing with an air inlet and an air outlet, wherein the fuel-oil heat exchanger is arranged at least partially within the housing such that air flowing from the air inlet to the air outlet can flow over or around the fuel-oil heat exchanger. The invention further relates to a method for operating an aircraft engine.

Abstract: An aircraft with a jet engine that has a radially outer engine cowling and an auxiliary gear appliance that has multiple auxiliary devices and that can be driven by a shaft that is in operative connection with an engine shaft that rotates about a central axis. The auxiliary gear appliance is arranged in the radial direction of the jet engine at least partially outside the outer engine cowling of the jet engine.

Abstract: A jet engine with a linking device for linking the jet engine at an element of an aircraft optionally in a first mounting position and at least one second mounting position, and with at least one operating equipment appliance that has a first fluid area and a second fluid area. In the first mounting position, the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality. In the second mounting position, the fluid areas are assigned to the respectively other functionality. What is further described is an aircraft with at least one such jet engine.

Abstract: A device for carrying out a chemical reaction by a continuous method has a reactor with at least two reactor sections which define a direction of flow. The reactor has plug flow properties along the direction of flow. A recirculation line is present to withdraw a partial flow from the reactor at a first point and return it to the reactor at a second point located above the first point in the direction of flow. Means are provided which prevent a temperature increase in the reactor over a predetermined temperature range, for example change of more than approximately 50 K.

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 engine with a fuel supply appliance and with at least one hydraulic fluid circuit that includes a hydraulic fluid reservoir, and with a heat exchanger. In the area of the heat exchanger, thermal energy can be exchanged between the hydraulic fluid conducted inside the hydraulic fluid circuit and the fuel of the fuel supply appliance. The pressure inside the hydraulic fluid circuit is higher in the area of the heat exchanger than the pressure in the fuel supply appliance. The heat exchanger is connected to the hydraulic fluid reservoir. Outer walls of the heat exchanger and outer walls of the hydraulic fluid reservoir at least partially shield an overlap area between the heat exchanger and the hydraulic fluid reservoir against an environment of the heat exchanger and of the hydraulic fluid reservoir.

Abstract: A seat assembly for a motor vehicle includes a seat cushion and an output shaft rotatably coupled to the seat cushion. An actuator is fixedly coupled to the seat cushion and operatively coupled to the output shaft for rotatably driving the output shaft. A front leg is operably connected to the actuator for movement between a support position supporting the seat cushion and a retracted position folded underneath the seat cushion. A front latch is mounted on the front leg and is positioned to selectively engage a striker bar along a motor vehicle floor for maintaining the front leg in the support position. A link assembly extends between the output shaft and the front latch for selectively unlocking the front latch as the output shaft is rotatably driven by the actuator to drive the front leg between the retracted position and the support position.

Abstract: A seat assembly for a motor vehicle includes a seat cushion and an output shaft rotatably coupled to the seat cushion. An actuator is fixedly coupled to the seat cushion and operatively coupled to the output shaft for rotatably driving the output shaft. A front leg is operably connected to the actuator for movement between a support position supporting the seat cushion and a retracted position folded underneath the seat cushion. A front latch is mounted on the front leg and is positioned to selectively engage a striker bar along a motor vehicle floor for maintaining the front leg in the support position. A link assembly extends between the output shaft and the front latch for selectively unlocking the front latch as the output shaft is rotatably driven by the actuator to drive the front leg between the retracted position and the support position.