摘要:
The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the bypass duct forming with the radially outer bypass wall a bypass nozzle, and with the radially inner wall including an adjusting element extending along the circumference of the inner wall and being deformable radially outwards.
摘要:
The present invention relates to a gas-turbine exhaust cone having an outer wall, which is provided with a plurality of recesses, a honeycomb-structured layer, which is arranged on the inside of the outer wall and extends along the inside of the outer wall, an inner wall, which extends substantially parallel to the outer wall and is connected to the honeycomb structure, and at least one annular chamber, which adjoins the inner wall and is centered relative to a central axis, with the inner wall being provided with passage recesses connecting the area of the honeycomb structure to the annular chamber.
摘要:
An ejector nozzle tube, having along its length an essentially constant, essentially oval hollow cross-section, with a leading edge nozzle, having a rounded exterior cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube. The leading edge nozzle includes a plurality of grooves issuing to the top and bottom sides of the ejector nozzle tube and connecting to an interior of the ejector nozzle tube formed by the hollow profile. An aircraft engine has an optimized oil heat exchanger with at least one oil cooler disposed in a trailing-edge area of an aerofoil-type structure, with at least one flow entrance area being provided to supply ambient air to the oil cooler disposed in a flow duct. The ejector nozzle tube can be arranged downstream of the oil cooler in the flow duct.
摘要:
The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling, the rear area of which can be displaced 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 free space towards a forward stationary area of the engine cowling, with the rear area of the engine cowling being functionally coupled to deflecting elements arranged in the forward thrust position within the front area of the engine cowling, with the deflecting elements during displacement of the rear area of the engine cowling being moveable on a partial-circular path facing the central axis of the engine and contactable by their rear end areas with a cowling of the core engine.
摘要:
An arrangement (1) for suspending a jet engine (12) to a supporting structure (5) attached to an aircraft fuselage, includes a suspension beam (6) to which the engine casing (13) is fitted by a forward suspension (7), a rearward suspension (8) and at least one thrust rod (9) arranged at an angle relative to the suspension beam (6). In order to provide an arrangement for the suspension of a jet engine (12) which enables weight to be saved and deformation of the jet engine (12) to be reduced, the rearward suspension (8) and the thrust rod (9) are connected to the engine casing (13) by a lightweight framework (11).
摘要:
An aircraft de-icing device and an engine nacelle of an aircraft gas turbine is provided with a de-icing device, with the engine nacelle 1 in the inflow area being provided with an annular air duct 2, into which heated air is introduced. At least one oil cooler 3 is arranged in the engine nacelle 1, to which engine oil is fed and which is supplied with ambient air, with the heated airflow leaving the oil cooler 3 being passed through the air duct 2.
摘要:
An arrangement (1) for suspending a jet engine (12) to a supporting structure (5) attached to an aircraft fuselage, includes a suspension beam (6) to which the engine casing (13) is fitted by a forward suspension (7), a rearward suspension (8) and at least one thrust rod (9) arranged at an angle relative to the suspension beam (6). In order to provide an arrangement for the suspension of a jet engine (12) which enables weight to be saved and deformation of the jet engine (12) to be reduced, the rearward suspension (8) and the thrust rod (9) are connected to the engine casing (13) by a lightweight framework (11).
摘要:
The present invention relates to an aircraft gas-turbine engine with a core engine surrounded by a bypass duct, with a radially outer engine cowling enclosing the bypass duct and being provided at its rear region with a thrust-reversing device which is moveable relative to the engine cowling, with at least one cooler element extending over at least part of the circumference being arranged in the intermediate area between the engine cowling and the thrust-reversing device.
摘要:
The present invention relates to a method for manufacturing a body provided with a honeycomb structure, which body is designed preferably axis-symmetrical, with sheet-metal parts being provided with a wave-like structuring by means of a forming process and formed to ring elements, with the sheet-metal parts being shaped and designed in a substantially identical way as regards their structuring, with adjacent sheet-metal parts being arranged offset to one another and then joined together to form the honeycomb structure.
摘要:
A method for manufacturing a sound absorber, the outer wall of which is provided with a plurality of recesses, with funnel-like cone elements each being assigned to the recesses inside the sound absorber, said cone elements having a larger opening facing radially outwards and a smaller opening facing radially inwards, with adjacent cone elements each being provided on a strip-shaped first carrier band, with cup elements being provided radially on the inside relative to the cone elements, and each cup element receiving one cone element, with adjacent cup elements each being provided on a strip-shaped first carrier band, with the first carrier bands being arranged adjacently in a first direction, and the second carrier bands being arranged adjacently in a second direction, with the directions crossing each other and the carrier bands being joined to one another and to the outer wall to form a rigid body.