Abstract: An engine has a shroud which surrounds one of a propfan and a propeller having blades. The shroud has a variable geometry. A direction of the air flow inside a duct of the shroud is reversible via an adjustment of the blades for the reversal of the thrust of the engine. A separately movable nozzle ring forms a rearward end of the shroud. The nozzle ring is axially displaceable to an extent such that its trailing edge forms wherein air flow is promoted around the end of the shroud.

Abstract: A turbofan engine includes two oppositely rotating fan rotors which are arranged upstream of the core engine, and has a booster with two contra-rotating coaxial rotors. The radially exterior booster rotor is arranged between the rearward fan rotor and the low-pressure turbine in a torque-transmitting manner. The gearless construction permits an almost uniform loading of the low-pressure shafts.

Abstract: A propfan engine having two oppositely rotating fan rotors both driven by a low-pressure turbine by way of a drive shaft includes a reversing transmission. The reversing transmission drives one fan rotor, while the other fan rotor is coupled directly to the drive shaft. This construction permits a favorable design of the rotational speeds of the fan rotors and of the turbine and, in comparison to a conventional transmission, requires less space and weight for both fan rotors.

Abstract: A gas turbine jet engine is disclosed with a fan delivering into a bypass duct to generate mainly propulsion thrust, and with a thrust reversing device having flaps which for reverse thrust operation pivot into the fan air stream and cooperate with an axially extended extreme section of the outer wall of the bypass duct to uncover delection ports arranged at breakthroughs in the outer wall. The extreme section of the outer wall and the thrust reverser flaps are linked one with the other for relative movement between them such that in a first phase of actuation relative to a fixed extreme nozzle section, the extreme section provides an additional fan nozzle area which communicates with the inlet flow areas formed by the flaps relative to the bypass duct.

Abstract: An arrangement for the adjusting of rotor blades of a propfan turboprop engine equipped with two counter-rotating propfan rotors has a number of double-toothed planet wheels which are fastened in a rotatably disposed web. The web is supported on the side of the housing by planet members disposed on one of the propfan rotors. The two toothings of the planet wheels are in operative connection with ball spindle adjusting rings. Using an adjusting motor, a relative movement of the web can be achieved with respect to the housing, whereby the blades of two counter-rotating rotor blade rings can be swivelled. According to the invention, an adjustment of rotor blades will also be possible when no stationary housing parts are available for the support.

Abstract: In an arrangement for mounting a shrouded pivotable propfan blade at a rotor, the propfan blade is held in a dovetail mounting of a blade carrier and, by using a first securing device is fixed with respect to axial movements of the propfan blade. The blade carrier is secured with respect to radial movements by means of a second securing device, which is accessible from the outside. This permits a simple and fast mounting and demounting of the propfan blades.

Abstract: A turbo engine with a gas turbine to drive propellers or propfan blades is disclosed which includes a speed reduction transmission interposed behind the gas turbine output drive shaft and the propellers or propfan blades. A cooling air impeller is provided to provide the supply of cooling air to an oil cooler for the speed reduction transmission. The impeller is arranged directly on the turbine output drive shaft.

Abstract: A propfan turbine engine having a reduction gearing for the propfan rotors is provided with a lubricating system of its own for the reduction gearing, the system being arranged axially between the gas turbine and the reduction gearing and formed as an annular assembly surrounding a drive shaft from a gas turbine to the reduction gearing. Cooling air is supplied to the lubricating system as a location which will not interfere with the supply of air to the compressor of the gas turbine.

Abstract: A bearing arrangement between shafts of a fluid flow engine, especially including a high pressure turbine and/or a lower pressure turbine, includes a damping gap for the controllable formation of a carrier film between an outer bearing race and a bearing mounting member. A damping fluid is introduced into the damping gap of a squirrel cage bearing. The outer bearing race rotates with an r.p.m. corresponding to that of the high pressure turbine shaft r.p.m. or to that of the low pressure turbine shaft r.p.m. The damping fluid is supplied through a channel passing through the low pressure turbine shaft and into an entrapment chamber just at the entrance end of the damping gap, whereby the rotation of the entrapment chamber compresses the damping fluid by a centrifugal force into the damping gap.