Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Olivier Pelagatti

Damien Prat

Thomas Deguin

Ronan Bodet

Amadou André Sylla

Amadou Andre Sylla

Jerome Huber

Franck Crosta

Jérôme Huber

Klaus Debatin

Jérome Hubert

A turbojet comprising a low-pressure compressor, a high-pressure compressor and a bleeding system configured to bleed air in the turbojet and to deliver the air to an air system. The bleeding system comprises a first air intake configured to bleed air at low pressure, a second air intake configured to bleed air at high pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to an outlet of the second valve, a high-pressure valve connected to the second air intake, a control valve connected to the air system, and a controller to control opening and closing of the valves depending on a pressure at the first air intake.

Turbojet comprising a bleeding system for bleeding air in said turbojet

A turbojet comprising a high-pressure compressor with several compression stages in which the pressure rises in a direction of air flow, from a low pressure to a high pressure, passing through intermediate pressures, and a system to bleed air in the turbojet and deliver the air to an air system. The bleeding system comprises a first air intake to bleed air at low pressure, a second air intake to bleed air at an intermediate pressure, a first valve and a second valve having inlets connected to the first air intake, a compressor having an inlet connected to the second valve outlet, a high-pressure valve connected to the second air intake, and a control valve connected to the air system, and a controller to control the opening and closing of the valves depending on the pressures at the first and second air intakes.

According to the invention, the shape of each of said chevrons is defined: by two lateral sides () having front ends (A,A) that are connected to said nozzle () and that, when moving away from the latter, converge towards each other without joining so that the rear ends (R,R) of said lateral walls () are spaced from each other; and by a curvilinear transverse line () connecting the rear ends (R,R) of said lateral walls () by forming two rounded side protrusions () separated by an intermediate rounded recess ().

Noise control chevron for a nozzle, and nozzle and turboshaft engine provided with such a chevron

According to the invention, a plurality of embossments () having a rectangular section is provided at the inner periphery of the outlet opening () of the fan duct (), said embossments being separated by longitudinal channels () having a convergent (C) and a divergent (D) for the cold flow ().

Turboshaft engine with reduced noise emission for aircraft

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Toulouse, France

Olivier Pelagatti