Safran Aero Boosters Sa

General Electric Company

Safran Aero Boosters

Rémy Henri Pierre Princivalle

Julien Marande

A stator assembly including an upstream blade and a downstream blade axially overlapping and defining between them a channel. The inlet surface of the channel is greater than or equal to the outlet surface of the channel, preferably with a factor of 2. A turbomachine provided with such an assembly, arranged upstream of a high-pressure compressor.

Tandem stator

A turbomachine of the type with an unducted fan, comprising: a separation nozzle splitting an air flow into a primary flow and a secondary flow; a compressor compressing the primary flow; and an air/oil heat exchanger; wherein the exchanger is positioned in a channel through which a tertiary flow passes, the tertiary flow being drawn from the secondary flow upstream of the exchanger and meeting at least one annular row of rotor blades of the compressor downstream of the exchanger.

Turbomachine structure with three air flows

A method and system control the thrust of an aircraft turbomachine having a high bypass ratio by direct action on a variable-pitch system. The variable-pitch system varies the pitch of the vanes of a stator of a low-pressure compressor for the open-loop control of the thrust of the turbomachine. The method also provides closed-loop control of the pitch of the blades of a propeller based on a rotational speed of the propeller.

Method and system for regulating the thrust of an aircraft turbomachine

A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.

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Herstal, Belgium

Rémy Henri Pierre Princivalle