Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Munchen Gmbh

Motoren- Und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union

Alois Rohra

Helmut A Geidel

Heinrich Enderle

Helmut-Arnd Geidel

Klaus Rud

Klaus Britz

Peter Tracksdorf

Helmjut-Arnd Geidel

Martin Cempirek

Thrust reverser for a propfan engine

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.

Turbofan engine having a contrarotating low-pressure compressor

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.

Propfan engine having two oppositely rotating fan rotors

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.

Thrust reverser for turbofan engine

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.

Arrangement for adjusting the rotor blades of a propfan turboprop engine

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.

Arrangement for mounting a pivotable propfan blade

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.

Turbo engine

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.

Growing community of inventors

Munchen, Germany

Alois Rohra