公开(公告)号：US10760696B2

公开(公告)日：2020-09-01

申请号：US16095154

申请日：2017-04-20

Applicant: Safran Aircraft Engines

Inventor： Clement Bernard ,  Loic Pora ,  Christophe Cebille

IPC: F16K11/07 ,  F15B13/04 ,  F02C7/232 ,  F15B13/00

Abstract: A slide for a fuel circuit valve of an aircraft engine extending along a longitudinal axis, and comprising a narrowed intermediate portion extending between two cylindrical end portions, a first end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate portion including in turn, as an extension of the shoulder, at least one cylindrical portion, the shoulder comprising at least one groove which extends radially from the cylindrical surface of the first end portion, towards the longitudinal axis, and which forms a fuel recirculation area which provides the generation of a jet of fuel on the cylindrical portion of the narrowed intermediate portion, when fuel flows along the first end portion towards the narrowed intermediate portion and the second end portion.

公开(公告)号：US10690264B2

公开(公告)日：2020-06-23

申请号：US16095187

申请日：2017-04-20

Applicant: Safran Aircraft Engines

Inventor： Clement Bernard ,  Loic Pora ,  Christophe Cebille

IPC: F16K47/08 ,  F16K11/07 ,  F15B13/04 ,  B64D33/00 ,  F16K31/06 ,  F15B13/00

Abstract: A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.

公开(公告)号：US11691751B2

公开(公告)日：2023-07-04

申请号：US16469019

申请日：2017-12-15

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Loic Pora

IPC: B64D37/00 ,  F02C7/22 ,  F16L55/07 ,  F15B1/02

CPC classification number: B64D37/005 ,  F02C7/222 ,  F16L55/07 ,  F05D2260/96 ,  F15B1/021 ,  F15B2201/3153 ,  F15B2201/405

Abstract: An accumulator designed to damp the pressure waves of the hydraulic shocks originating in a downstream section of a duct is arranged inside the duct, with the opening of the accumulator pointing downstream. This results in excellent absorption of the pressure wave and protection of the circuit from possible accumulations of air, water or ice, there being no areas where the flow stagnates. Immersing the accumulator in the flow also makes it possible to ensure that the equipment is protected in the event of a fire.

公开(公告)号：US11365692B2

公开(公告)日：2022-06-21

申请号：US16630705

申请日：2018-07-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Loic Pora ,  Arnaud Bernard Clement Thomas Joudareff

IPC: F02C9/26 ,  F02C7/232

Abstract: A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit.

公开(公告)号：US11105271B2

公开(公告)日：2021-08-31

申请号：US16311407

申请日：2017-06-27

Applicant: Safran Aircraft Engines

Inventor： Loic Pora

IPC: F02C9/38 ,  F02C7/232 ,  F02C9/32 ,  F02C7/22 ,  F16K11/07

Abstract: A circuit for metering fuel for a turbomachine, including a fuel metering element, a pump designed to pump a flow of fuel to the metering element, and a control valve designed to return, toward the pump, an excess flow of fuel delivered to the metering element as a function of a fuel pressure difference at the terminals of the metering element, the control valve is designed to modulate the excess flow returned toward the pump as a function of variations in the density of the fuel delivered to the metering element. A turbomachine can include such a circuit.

公开(公告)号：US12037947B2

公开(公告)日：2024-07-16

申请号：US18248666

申请日：2021-10-05

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Kevin Didier Pierre Le Normand ,  Frederic Brettes ,  Loic Pora

IPC: F02C7/22 ,  F02C7/232 ,  F02C7/236 ,  F23R3/28 ,  F23R3/34

CPC classification number: F02C7/222 ,  F02C7/232 ,  F02C7/236 ,  F23R3/283 ,  F05D2220/323 ,  F05D2240/35 ,  F23R3/34

Abstract: A device for distributing at least one fuel flow for a circuit for supplying fuel to a combustion chamber of a turbo machine, in particular of an aircraft, the device including a rotating main body extending about a longitudinal axis, the main body including an internal flow duct for a first flow of fuel, extending through the main body along the axis, a first annular portion configured to form an outlet passage for a second flow of fuel, and including at least one orifice for the second flow of fuel to pass through, and an external annular groove in fluidic communication with the at least one orifice in the first portion.

公开(公告)号：US11905885B2

公开(公告)日：2024-02-20

申请号：US18248665

申请日：2021-10-05

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Kevin Didier Pierre Le Normand ,  Frederic Brettes ,  Loic Pora

IPC: F02C7/232 ,  F02C7/22 ,  F02C7/236

CPC classification number: F02C7/232 ,  F02C7/222 ,  F02C7/236 ,  F05D2220/323 ,  F05D2240/35

Abstract: A fuel supply circuit including a supply duct in which a first flow (Fl) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (Fl), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump.

公开(公告)号：US11867076B2

公开(公告)日：2024-01-09

申请号：US17595473

申请日：2020-05-18

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Loic Pora ,  Huguette De Wergifosse

IPC: F01D25/18 ,  F01M1/02 ,  F01M1/12 ,  F01M1/16 ,  F16H57/04 ,  F01M11/00

CPC classification number: F01D25/18 ,  F01M1/02 ,  F01M1/12 ,  F01M1/16 ,  F16H57/0475 ,  F01M11/0004 ,  F01M2001/0246 ,  F01M2001/0253 ,  F01M2001/123 ,  F16H57/0441

Abstract: The invention relates to a system (1) for lubricating an aeronautical engine (5) and a reduction gearbox (4) associated with the engine (5), the system (1) comprising an oil reservoir (2) feeding at least one first supply pump (3) supplying a first circuit (6) of the gearbox (4) opening into at least one chamber (4a) of the gearbox (4) and, in parallel, a second circuit (7) of the engine (5) opening into chambers (5a) of the engine (5). The second circuit (7) comprises a jet pump (9) of variable cross section supplied at least by the first supply pump (3), bypassing the first circuit (6), a second driven supply pump (10) being integrated into the second circuit (7) downstream of the jet pump (9), a portion of a flow (Qp) in the first circuit (6) being drawn off by the jet pump (9) to supply the second circuit (7).