Safran Aircraft Engines

Yannick Schini

Arnaud Rodhain

Arnaud Baudran

Eric Charles Pean

A fuel pressure accumulator for a fuel supply circuit of a turbine engine having at least one pipe is provided. The fuel pressure accumulator generally includes at least one housing adjacent to said pipe and receiving at least one deformable enclosure confining a gas and having at least one movable wall in contact with the fuel in order to dampen a fuel overpressure, where the housing is coaxial with the pipe and the accumulator has a permeable chamber delimited at least partially by the housing, pressurizing the deformable enclosure and communicating with the main fuel flow via a grid with staged walls tilted, with respect to a direction of the flow flowing along the grid, substantially in the direction of the deformable enclosure.

Accumulator integrated into a fuel line

The present invention concerns a method for starting a test testing the operation of at least one fan designed to cool at least one computer of an aircraft turbojet engine, said method comprising steps of:&#x2014;comparing (E) the number of flights carried out by said aircraft since the last operation of the fan (N) with a first threshold (y),&#x2014;comparing (E) the number of flights carried out by said aircraft since the last operation of the fan (N) with a second threshold (x), said second threshold being greater than or equal to the first threshold,&#x2014;acquiring an environmental parameter (T) and checking if the parameter satisfies a limit environmental condition of operation of the fan (E),&#x2014;controlling (E) the starting of said fan operation test when the number of flights carried out by said aircraft since the last operation of the fan (N) is greater than or equal to said first threshold (y), less than said second threshold (x) and when the acquired parameter (T) satisfies said limit environmental condition.

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Paris, France

Yannick Schini