Turbojet engine with thrust resistance on intervening compressor housing

Abstract

The invention relates to a multi-flow turbojet comprising: a. an upstream fan (2) driven by a gas generator, b. a gas generator comprising a coaxial first compressor (3) and a second Second compressor (4), c. Inlet housing (8), which forms the support for the rotor of the fan (2) and the rotor of the first compressor (3), d. The intermediate compressor housing ( 9) which is located downstream of the inlet casing (8) and forms a support for the rotor of the second compressor (4), e. attachment means for thrust resistant coupling rods (95) , the device is arranged on the intermediate compressor housing. The turbojet engine is characterized in that the turbojet engine comprises at least one coupling rod (32) connecting the inlet housing (8) to the intermediate compressor housing (9) for transmitting axial loads.

Description

technical field [0001] The invention relates to the field of aeronautical propulsion. The present invention relates to the suspension of a turbojet engine onto an aircraft, and more particularly to the arrangement of the transmission or thrust absorption provided by the engine to the structure of the aircraft. Background technique [0002] The prior art includes in particular documents CA-A1-2 929 947 , EP-A2-2 610 462 , WO-A2-2008 / 000924 and FR-A1-3 007 458 . [0003] The multi-flow turbocharged engine according to the architecture of the prior art comprises, from upstream to downstream in the direction of the air flow through the turbojet engine, a ducted fan and a gas generator, by means of which the multi-flow turbocharged engine The duct fan and gas generator are rotationally driven. The gas generator consists of at least one compressor, an annular combustion chamber, at least one turbine and a combustion gas exhaust pipe. The air compressed by the ducted fan is divi...

AI Technical Summary

Problems solved by technology

This is not without consequences: the BP compressor casing has low mechanical strength, and the axial stresses corresponding to the thrust absorption on the casing can lead to deformations, as a result of which, on the one hand, the clearance of the leading blades is increased, resulting in a loss of efficiency, or On the other hand, the clearance of the front blades is reduced, creating a risk of stator / rotor contact

[0012] The low mechanical strength of the BP compressor can be compensated by using the same material to increase its thickness, which leads to an increase in weight

However, as long as the stress propagates through it, deformation can be observed with the above mentioned consequences

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