Snecma

Arianegroup Sas

Jean Michel Sannino

François Danguy

Nicolas Soulier

David Hayoun

Jean-Luc Barthoulot

François Lassoudiere

Stéphanie Dreyer

Pascal Marcel Jean Noir

Antoine Caratge

The invention relates to a feed device for feeding a thrust chamber () of a rocket engine () with first and second propellants. According to the invention, a first feed circuit () of the thrust chamber () comprises a turbopump () having at least one pump () for pumping the first propellant from a first tank (), and a turbine () mechanically coupled to said pump (). The first feed circuit connects an outlet of the pump to an inlet of the turbine via a heat exchanger () configured to heat the first propellant with heat generated by the thrust chamber, in order to actuate the turbine. According to the invention, a second feed circuit () is configured to feed the thrust chamber with second propellant from a second tank () that is configured to be pressurized. The invention also provides a method of feeding a rocket engine thrust chamber with first and second propellants.

Method and a device for feeding a rocket engine

A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.

Pressurizing device and method

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Saint-Marcel, France

Jean Michel Sannino