Patent ID: 7950218

Claim:
A bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and with an annular nacelle centered on the longitudinal axis of the turbomachine and surrounding the engine in such a manner as to co-operate therewith to define an annular channel along which a cold stream flows on passing through the turbomachine, the nacelle having an upstream end surrounding the fan of the engine and a stationary downstream end forming a nozzle for ejecting the gas from the turbomachine, the nozzle having a throat section corresponding to its smallest cross-section, the turbomachine further comprising: channel air intake means for taking air from the cold stream flow channel upstream from the throat section of the nozzle; channel air injector means for injecting the taken-in channel air downstream from the nozzle throat section so as to open the throat section artificially; outside air intake means for taking air from outside the turbomachine and for compressing said outside air; and outside air injector means for injecting the taken-in air into the vicinity of the throat section in a direction that is substantially perpendicular or opposite to the flow direction of the air stream in the cold stream flow channel so as to close the throat section artificially by aerodynamically obstructing the flow rate of air passing therethrough, wherein the outside air intake means comprise at least one outside air inlet open to the outside of the turbomachine and connected to an inlet of a pump having a compressor module and housed inside the gas turbine engine.