Safran Aircraft Engines

Snecma

Loïc Pora

Huguette De Wergifosse

Eric De Wergifosse

Sébastien Christophe Loval

Frédéric Brettes

Petar Tomov

Arnaud Bernard Clément Thomas Joudareff

Christophe Cebille

Bastien Dore

Kevin Didier Pierre Le Normand

Théodore Magne

Virgile Nicolas Bastien Garnier

Petar Dimitrov Tomov

Clément Bernard

The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, a fuel circuit includes a pressurisation valve at an outlet of the system and a pump. The circuit may include a flow rate sensor arranged between the outlet of the pump and the pressurisation valve. In some embodiments, the flow rate sensor may include a sliding drawer, a restoring spring, and a sensor for detecting the position of said drawer in order to indicate the flow passing through the flow rate sensor. The system may include a device arranged to drive the pump with a controllable rotational speed and a control configured to control the device on the basis of a measurement supplied by the flow rate sensor, in such a way as to adapt the rotational speed of the pump shaft.

System for supplying fuel to a turbomachine

The invention relates to a method for metering fuel in a fuel supply circuit of an aircraft engine, the circuit comprising a metering device for a fuel circuit of an aircraft engine comprising, downstream of a fuel pumping system and upstream of injectors: —a fuel inlet (E), —a metering device (FMV) and a cut-off device (HPSOV) arranged in series, —an adjustment valve (VR) arranged on a fuel recirculation branch, such that any excess fuel supplied by the pumping system is fed back into the fuel circuit, wherein at least one flow-metric sensor (WFM) is arranged on the recirculation branch, a density value for the metered fuel is determined according to the sensor measurements and the metering device is controlled according to the fuel density value thus determined.

Method for determining the density of fuel for metering fuel in a fuel supply circuit of an aircraft engine

Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.

Aircraft engine fuel pump

The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, the system includes a pump, a hydromechanical group, a drive device positioned to drive the pump, and a branch comprising actuators for controlling variable geometry. In some embodiments, the system regulates a fuel flow rate based at least in part on a flow rate set point value. In some embodiments, the system may include a flow rate sensor. A flow rate loop may be arranged to determine a pressure set point value at the outlet of the pump according to the flow rate set point value and a measurement supplied by the flow rate sensor. In some embodiments, a pressure sensor may be positioned in the fuel circuit at the outlet of the pump. In further embodiments, a pressure loop may control the speed of the drive device based at least on a difference between a pressure measurement supplied by the pressure sensor and the pressure set point value.

Circuit for supplying fuel to a turbomachine

Device () for testing a hydraulic part () for a turbomachine, the device comprising a closed loop for circulation of a working fluid, the loop comprising at least one recirculation pump () configured to circulate the working fluid in the loop according to a direction of circulation, at least one valve () for regulating the flow rate of a working fluid, at least one reservoir (A) configured to store the working fluid, a test section () configured to accommodate the hydraulic part (), the device () further comprising a gas injection means () configured to inject and dissolve, at atmospheric pressure, a gas in the working fluid stored in the reservoir (A).

Device and method for improved testing of a hydraulic part for a turbomachine

A jet pump () is inserted between the low-pressure pump and a high-pressure fuel pump (). A fuel metering unit () includes a metering valve () which delivers a regulated fuel flow to a feed line (), and a bypass valve () which diverts to a primary intake () of the jet pump the excess fuel flow supplied by the high-pressure pump. An overspeed protection unit () includes a control element () of the bypass valve () which causes said to fully open in the event of an overspeed of the engine. A shutoff and pressurization checkvalve () is mounted on the feed line and controlled by a servo-valve () having a high-pressure port () brought to the high fuel pressure, a low-pressure port brought to the pressure of the primary intake () of the jet pump and an output setting the pressure in a control chamber () of the shutoff valve () to a value between those prevailing at the high pressure and low pressure ports. In the event of overspeed, the restriction imposed by the jet pump causes a pressure rise at the primary intake of the jet pump, hence a pressure rise in the control chamber of the shutoff valve (), favoring the closing thereof.

Growing community of inventors

Moissy-Cramayel, France

Loïc Pora