Snecma

Arianegroup Sas

Centre National Detudes Spatiales

François Danguy

Dominique Valentian

Damien Feger

Philippe Bourdin

Alban Lemaitre

Emmanuel Edeline

Laurent Fabbri

Jean-Michel Nguyen Duc

Fabien Wahl

David Hayoun

Jean Michel Sannino

Sebastien Guingo

Vincent Langlois

Cëdric Sene

Stéphane Laffite

Valérie Begin

Manuel Frocot

Noël Marchal

Olivier Lagnel

Pascal Marcel Jean Noir

Frédéric Boudehen

Vincent Pendaries

Sébastien Guingo

Cédric Sene

Julien Kohler

The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump () comprising at least: an impeller (); a rotary shaft () secured to said impeller (); a casing () having an axial admission passage (); at least one first bearing () supporting said rotary shaft () in said casing (); and at least one dynamic seal () around the rotary shaft (), the impeller () being situated between the at least one dynamic seal () and the axial admission passage () of the pump (). The centrifugal pump () also comprises, between the impeller () and at least one dynamic seal (), an axial force compensation disk () secured to the shaft () and presenting a diameter greater than 70% of a diameter of the impeller (). A front face () of the disk () faces towards the impeller () and is connected to a branch connection for fluid under pressure taken downstream from the pump (), and a rear face () faces towards the dynamic seals () and presents fins () that are oriented radially, at least in part.

Centrifugal pump, in particular for supplying power to rocket engines

A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.

Turbopump, in particular for feeding rocket engines

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

A turbomachine arranged with a rotor and a stator, including a radial positioning device ensuring that the rotor is radially positioned; and a contactless axial balancing device arranged on at least one bladed wheel for axially balancing the rotor at high speed. The turbomachine includes a thrust bearing distinct from the radial positioning device serving to balance the rotor axially at low speed, and without contact at high speed. In addition, the radial positioning device is constituted by hydrostatic bearings, the turbomachine including hydrostatic bearing feed circuits suitable for connecting the bearings to a source of fluid under pressure. As a result, it is possible to obtain operation at high speeds with a very long lifetime.

Turbomachine with a long lasting position-holding system

A pump for the drawing-in of a fluid, including at least one centrifugal wheel having a fluid inlet edge and a fluid outlet edge, the pump further including an axial balancing system with a high-pressure flow space defined between the housing and an upstream face of the centrifugal wheel. The axial balancing system further includes a device for substantially increasing the hydrostatic pressure of the fluid circulating in the high-pressure flow space during operation of the pump.

Pump comprising an axial balancing system

The compressor-evaporator system for liquefied gas contained in a tank comprises, in addition to a deice for evaporation by heat exchange with a liquid and devices for conditioning and transferring gas to a pipeline, a motor-driven turbopump comprising a rotary assembly of high bending stiffness on a common shaft line, with at least one high pressure pump, a turbine, and a central electrical machine capable of being used in motor mode or in generator mode. The rotary assembly of the motor-driven turbopump is adapted to present a high speed of rotation, greater than 12,000 rpm, while remaining outside ranges for exciting critical speeds in rotation. All of the internal portions of the motor-driven turbopump are immersed in a cryogenic fluid that is the same as the liquefied gas contained in the tank. The internal cavities of the motor-driven turbopump that are under different thermodynamic conditions are separated by contactless dynamic seals. Electronic power circuits connected to an electricity network control the central electrical machine in motor mode or generator mode.

Compression-evaporation system for liquefied gas

Growing community of inventors

Tourny, France

François Danguy